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1. 5 11 FUEL CONSUMPTION 5 12 CRUISEPERFORMANCE 5 13 LANDING PERFORMANCE 5 14 Page Date 20 April 2002 5 1 Section 5 Pilot s Operating Handbook Performance XTRA EXTRA 300L Left blank intentionally 5 2 Page Date 20 April 2002 Pilot s Operating Handbook Section 5 EXTRA 300L XTRA Performance SECTION 5 PERFORMANCE 5 1 GENERAL Performance data charts on the following pages are presented to facilitate the planning of flights in detail and with reasonable accuracy under various conditions The data in the charts have been computed from actual flight tests with the aircraft and engine in good condition and using average piloting techniques It should be noted that the performance information presented in the range and endurance charts allow for 45 minutes reserve fuel at specified speeds Some indeterminate variables such as engine and propeller air turbulence and others may account for variations as high as 10 or more in range and endurance Therefore it is important to utilize all available information to estimate the fuel required for the particular flight 5 1 1 Performance Charts Performance data are presented in tabular or graphical form to illustrate the effect of diffe rent var
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3. 7 8 LANDINGGEAR 7 8 SEATS SEAT E 7 9 CANOPY 7 9 ue dd 7 10 7 10 Oll SYSTE 7 11 Engine InstallatiQh 7 11 Propeller ul 7 11 alu 7 11 7 12 EE 7 12 Fuel Selector I p kas 7 12 Exhaust Systems 7 12 PUBL SYSTEM u iu MH 7 12 ELECTRICAL SYSTEM rre iex e trennen nee eaae nne ix name Deko 7 13 CABIN ENVIRONMENT CONTROL J l 7 15 Page Date 20 September 2006 7 1 Section 7 Pilot s Operating Handbook Description and Operation of Aircraft and Systems lt X TRA EXTRA 300L Left blank intentionally 7 2 Page Date 20 April 2002 Pilot s Operating Handbook Section 7 EXTRA 300L X TRA Description and Operation of Aircraft and Systems SECTION 7 DESCPRIPTION AND OPERATION OF AIRCRAFT AND SYSTEMS 7 1 THE A
4. O O O 0 IO LO 0 TIN sr OLMIS 0 0 LO CO wem we qoem qm pem cO 00 LO LO co olo eig olo Manda 111 10054 v E v v E E v v lt E lt v 0 c lt Page Date 16 March 2009 Pilot s Operating Handbook XTR A EXTRA 300L Paragraph 2 1 2 2 2 3 2 4 2 4 1 2 4 2 2 5 2 6 2 7 2 7 1 2 7 2 2 7 3 2 8 2 8 1 2 8 2 2 9 2 9 1 2 9 2 2 10 2 11 2 11 1 2 12 2 13 2 14 2 14 1 2 14 2 2 14 3 2 15 2 16 SECTION 2 LIMITATIONS Table of Contents Page GENERAL SZ 2 3 D rezimz z PR 2 3 CROSS WIND COMPONENTT
5. 920 6 Selftests of the Unit 8 920 6 Selecion MOG MR 920 7 Flight Operation in Mode A C S reply code and altitude code 920 9 VER Gode Sua ua N au 920 10 Configuration 920 10 LIMITATIONS 920 10 EMERGENCY PROCEDURES 920 10 Important e 920 10 NORMAL PROCEDURES eire ueneno ee eec 920 10 PERFORMANCE gt 920 10 Page Date 31 March 2009 920 1 Section 920 mE Pilot s Operating Handbook BECKER BXP 6401 Transponder XTRA EXTRA 300L Left blank intentionally 920 2 Page Date 31 March 2009 Pilot s Operating Handbook 2 Section 920 EXTRA 300L BECKER BXP 6401 Transponder 920 1 GENERAL The Becker panel mounted BXP 6401 Transponderis a radio transmitter and receiver that fulfills the role of the airborne beacon equipment according to the requirements of the Air Traffic Radar Beacon System ATCRBS Its functionality includes replying to ATCRBS Mode A C and Mode S interrogations It operates on radar frequencies receiving ground radar interrogations
6. U u 922 8 HANDLING SERVICING MAINTENANCE 922 8 Page Date 5 December 2008 922 1 Section 922 mE Pilot s Operating Handbook Center Tank Increased Capacity X TRA EXTRA 300L Left blank intentionally 922 2 Page Date 5 December 2008 Pilot s Operating Handbook Section 922 EXTRA 300L X TRA Center Tank Increased Capacity 922 1 GENERAL The center fuel tank with an increased fuel capacity from 42 to 60 L is available ex factory for the fuselage fuel tank system of the EXTRA 300L 922 2 LIMITATIONS The following data deviate from the data given in Section 2 of this Handbook 922 2 1 Fuel Total fuel capacity 189L 49 9USgal Usable fuel capacity in the system 187L 49 4 US gal Acro amp center tank capacity 69L 18 2 US gal Usable fuel capacity for acrobatic 67L 17 7 US gal 922 2 2 Weight Limits Max allowed empty weight Normal category 729 kg 1607 Ib Acrobatic category 686 1512 Ib 922 2 3 Placards The following placards replace the existing placards FUEL SELECTOR VALVE WING TANKS usable 120 L 31 7 US GAL in both cockpits near selector valve handle CENTER ACRO TANK usable 67 L 17 7 05 CENTER TANK INDICATION Oe On the rear instrument panel BELOW 9 L 2 4 US GAL next to the fuel quantity i
7. pis no SseJg 0008 95110 19 je jo eese Jy iy e 10 26 78 1 xey pue dn 104 15 sse 1 29 11 1210 al 7600 056 1 suonpuo 5 o gt 9 apis no 02 OL 0 0 0 06 Or Page Date 19 April 2012 921 12 Pilot s Operating Handbook EXTRA 300L XTRA Section 921 Lycoming AEIO 580 B1A Engine 9216 WEIGHT AND BALANCE LOADING WEIGHTS AND MOMENTS ACRO amp CENTER TANK L kg US gal Ib 65 143 144 31 8 18 0 39 7 21 6 47 6 252 556 28 8 63 5 324 71 4 36 0 7933 39 6 87 3 43 2 95 2 46 8 103 2 49 7 109 6 kg x cm L Ib x in US gal 157 365 459 553 648 742 836 931 1026 1120 1215 1291 WINGTANK 7 2 15 9 81 8 63 5 95 3 127 0 158 8 190 5 Also refer to the Equipment List in Section 6 which has been revised 921 7 DESCRIPTION kg x cm Ib x in 360 Tei 1442 2164 2885 3607 4328 The AEIO 580 B1A engine is characterized by the following performance data Rated power at 2700 RPM 315 HP 234 9 kW Rated power at 2600 RPM 303 HP 225 9 kW Rated power at 2400 RPM 286 HP 213 3 kW 813 629 1257
8. 916 5 916 5 PERFORMANCE Ro suede ecc 916 5 Page Date 15 December 2005 916 1 Section 916 mE Pilot s Operating Handbook BENDIX KING KT 76A Transponder XTRA EXTRA 300L Left blank intentionally 916 2 Page Date 15 December 2005 Pilot s Operating Handbook 2 Section 916 EXTRA 300L XTRA BENDIX KING KT 76A Transponder 916 1 GENERAL The BENDIX KING KT 76A panel mountedtransponder receives interrogations at 1030 MHz and these trigger a coded response of radar pulses which are transmitted back to ATC at 1090 MHz The return reinforces your aircraft s image or blip on the controller s radar screen The 76A can reply to radar in any of 4096 preselected codes Each code is identified by a unique group of pulses With either an separate encoder the KT 76A also provides ground radar with continuos report of your altitude which are automatically updated in 100 foot increments NOTE The 76A owner accepts all responsibility for obtaining the proper license before using the transponder Function Selector Reply Light Code Windows KT 76A BENDIX KING Ident Pushbutton Control Knobs 91611 CODESELECTION The Identification Code selection is done with 4 ATCRBS Code Selector Knobs that provide 4 096 active identification codes Each of the 4 Code Selector Knobs selects a separate digit of the identification c
9. WN 009 005 00 0004 000 0009 0008 00 002 0000 0002 000r 00091 VSI SNISIQHO OL H3MOd 0 1 15 sn 99 IZ dJAH3S3H 0 1 9 1v9 SN HLT 1 1 WLOL 687 5602 096 LHOI3M NOILIGNOD 1334 SHH 2 51 33 0008 9H S lZ 2dM OSEZ WdY 759 39NUU 178 3SInu23 9 11135 uaMOd 0004 000 0009 0008 00001 00021 0008 1 00091 1333 11 Page Date 20 April 2002 Section 5 Pilot s Operating Handbook Performance XTRA EXTRA 300L 5 9 FUEL CONSUMPTION LITER STANDARD DRY HOUR 23 8 90 211 18 5 70 15 9 60 13 2 50 10 6 40 79 30 5 3 20 26 10 GAL HOUR SL 2000 4000 6000 8000 10000 12000 14000 16000 ft PRESSURE RLT PR EXAMPLE PA 8000 ft ISA POWER SETTING 65 ONM FUEL CONSUMPTION LITER gt 52 LTR HRS 13 7 GAL HRS gt 3 25 NM LTR 12 3 NM GAL 457 15 1 4 0 557 13 2 3 5 557 11 4 3 0 9 5 2 5 1 0 POWER SL 2000 4000 6000 8000 10000 12000 14000 16000 ft PRESSURE RLT PR 5 12 Page Date 20 April 2002 Pilot s Operating Handbook Se
10. 902 3 902 7 DESCRIPTION OF THE SYSTEM ccccicsevessseesiacesncccsensssqntvstencaceressepecsstsnnicccnattcnrtectecedice 902 3 902 8 HANDLING SERVICING AND MAINTENANCE 44 44 2221 902 4 Page Date 20 April 2002 902 1 Section 902 Pilot s Operating Handbook Electric Pedal Adjustment XTRA EXTRA 300L Left blank intentionally 902 2 Page Date 20 April 2002 Pilot s Operating Handbook Section 902 EXTRA 300L X TRA Electric Pedal Adjustment 902 902 1 902 2 902 3 902 4 902 5 902 6 902 7 ELECTRIC PEDAL ADJUSTMENT GENERAL To improve seat and control convenience the EXTRA 300 L can be equipped with an optional elect pedal adjustment system The pedal adjustment system provides an in flight capability to adjust the pedals according the pilots size and operation For example a more relaxed stretched seating position for long cross country flights is possible LIMITATIONS An adjustment of the pedal position during takeoff and landing is not allowed EMERGENCY PROCEDURES In case of an electric failure occurs during adjustment procedure e g unintentional contin ued adjustment by failure of a control switch try to move the pedals to the opposite direc tion immediately If this measure is unsuccessful the circuit breaker has to be pulled without delay The relative low actuation velocity enables the pilot to sufficient rudder contr
11. 912 7 LIMITATIONS jiet 912 8 EMERGENCY PROCEDURES 912 8 NORMAL PROCEDURES ire uiua deris 912 8 azizell bee 912 8 Page Date 15 December 2005 912 1 Section 912 mE Pilot s Operating Handbook FILSER TRT 600 Transponder XTRA EXTRA 300L Left blank intentionally 912 2 Page Date 15 December 2005 Pilot s Operating Handbook Section 912 EXTRA 300L XTRA FILSER TRT 600 Transponder 912 1 GENERAL The TRT 600 is Level 2es Class2 SSR Mode S Elementary Surveillance Transponder It has Mode A Mode A C and Mode S capability In Mode S the transponder provides acquisition capability Furthermore the TRT 600 has a built in barometric pressure altitude coder in 100 ft increments NOTE Refer to latest edition of Filser TRT 600 Pilot s Operation Manual Doc No 03 200 010 11 to get familiar with the TRT 600 Transponder The following illustration of the front panel of the TRT 600 will assist the operator to understand this Mode S Transponder Display or sat On Off Flight Di FID Rotating for 1000 Rotating for 1 Sguitter flag elimina Activa Test Monitor Battery flag t Displ ay Flight Level In Flight flag Standby Code Rotating knob for 10 Rotating knob IDENT for 100 Made Select
12. 1 3 TEGHINIGAL DATA L uu u uuu u u u a Lai R Das 1 3 DI WJ uk u 1 3 i 1 3 nen 1 4 Honzontal 1 4 asb wu 1 4 NEUEM 1 4 miUe 1 4 1 4 uuu N 1 5 Exhaust Systems Optional 001 sse nnne nnne nens 1 5 FUEL 1 5 ejm 1 5 HePtcmE 1 6 TERMINOLOGV E a 1 6 SECONDARY TERMINOLOGY u aS 1 7 2 5 20 1 ez n one qaqa uu 1 8 Page Date 16 March 2009 14 Section 1 Pilot s Operating Handbook General EXTRA 300L Left blank intentionally 1 2 Page Date 20 April 2002 Pilot s Operating Handbook Section 1 EXTRA 300L 1 0 DESCRIPTION The airframe of the EXTRA 300L is built of a tig welded steel tube construction
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14. Page Date 15 December 2005 914 3 Section 914 Pilot s Operating Handbook GARMIN GTX 327Transponder XTRA EXTRA 300L 914 1 2 CODE SELECTION Code selection is done with eight keys 0 7 that provide 4 096 active identification codes Pushing one of these keys begins the code selection sequence The new code will not be activated until the fourth digit is entered Pressing the CLR key will move the cursor back to the previous digit Pressing the CLR key when the cursor is on the first key of the code or pressing the CRSR key during code entry will remove the cursor and cancel data entry restoring the previous code The numbers 8 and 9 are not used for code entry only for entering a Count Down time and in Configuration Mode IMPORTANT CODES 1200 The VFR code for any altitude in the US Refer to ICAO standards elsewhere 7000 The VFR code commonly used in Europe Refer to ICAO standards 0021 The VFR code commonly used in Germany default is set to 0021 at time of installation 7500 Hijack code Aircraft is subject to unlawful interference 7600 Loss of communications 7700 Emergency 7777 Military interceptor operations Never squawk this code 0000 Military use Not enterable Care should be taken not to select the code 7500 and all codes in the 7600 7777 range which trigger special indicators in automated facilities Only the code 7500 will be decoded as the hijack code An aircraft s transponder code if a
15. SECTION 904 EMERGENCY LOCATOR TRANSMITTER Table of Contents Paragraph Page 904 1 GENERAL 904 3 904 2 LIMITATIONS 904 3 904 3 EMERGENCY PROCEDURES Cu nana Ta o De dama 904 4 904 4 NORMAL PROCEDURES 904 6 904 5 904 6 904 6 WEIGHT AND BALANCE L u i u 904 6 904 7 DESCRIPTION AND OPERATION OF THE 904 6 904 8 HANDLING SERVICING AND MAINTENANCE 4 4 444 22211 904 7 Page Date 20 April 2002 904 1 Section 904 mE Pilot s Operating Handbook Emergency Locator Transmitter X TRA EXTRA 300L Left blank intentionally 904 2 Page Date 20 April 2002 Pilot s Operating Handbook 2 Section 904 EXTRA 300L X TRA Emergency Locator Transmitter 904 EMERGENCY LOCATOR TRANSMITTER 904 1 GENERAL To improve the passive security the EXTRA 300 L can be equipped with an optional Emergency Locator Transmitter POINTER 3000 ELT This POINTER 3000 ELT transmit s automatically after a crash or manual activity on the emergency frequencies of 121 5 MHz civilian and 243 0 MHz military 904 2 LIMITATIONS The operation limitations are not effected due to the installation of the POINTER 3000 ELT For
16. Test Monitor Battery flag t Displ ay Flight Level In Flight flag Standby Code Rotating knob for 10 Rotating knob IDENT for 100 Made Select Exchange squawk coda STET 5 5 standby to active 913 1 1 FRONT PANEL OPERATION The input elements consist of four rotating knobs and five push buttons Page Date 15 December 2005 913 3 Section 913 Pilot s Operating Handbook FILSER TRT 800 Transponder XTRA EXTRA 300L ROTATING KNOBS Four rotating knobs are used to select the IDENT CODE The assignments X X X X indicate the position of the code number set by each knob PUSH BUTTONS ON OFF The unit can be turned on by pressing the ON OFF button for less then 1 second The unit can be turned off by pressing the ON OFF button for more then 2 seconds also refer to the System Operation Paragraph 913 1 2 MODE The following modes can be selected in sequence by pressing the MODE button STBY Standby Mode used for aircraft on ground with reduced squitter rate only Mode S with altitude reporting all ZERO only A S Mode A active with Mode C frames only and Mode S with altitude reporting all ZERO only ACS Mode and 5 full active ARROWS UP AND DOWN To activate the inserted SQUAWK CODE fromthe lower standby line to the upper active position the button with the UP AND DOWN ARROWS shall be pressed IDE
17. aias 905 4 905 8 HANDLING SERVICING AND 2 22 2222221 905 5 Page Date 20 April 2002 905 1 Section 905 junii Pilot s Operating Handbook External Power XTRA EXTRA 300L Left blank intentionally 905 2 Page Date 20 April 2002 Pilot s Operating Handbook Section 905 EXTRA 300L XTRA External Power 905 EXTERNAL POWER 905 1 GENERAL The EXTRA 300 L can be equipped with two versions of an optional external power receptacle system The normal system PN 93102 16 01 provides the capability to start the engine independent of the board battery and is limited to this use The continuous operation system PN 93102 16 02 further allows feeding the electrical system for longer periods 905 2 LIMITATIONS The operation limitations are not affected due to the installation of the external power receptacle system For the location of the external power receptacle and protection of the electrical connection cable against overheating the following placard has to be attached on the rear instrument panel with an indicator arrow to the receptacle EXTERNAL POWER 12V DO NOT CRANK FOR MORE THAN 10 SECONDS Allow 20 seconds to cool down between attempts Repeat up 6 times Then let starter cool for 30 minutes 905 3 EMERGENCY PROCEDURES Not affected 905 4 NORMAL PROCEDURES The following starting procedures are recommended however the starti
18. 6 3 1 Sample Take off Condition Pilot On Rear Seat 90 0 kg 198 5 Ibs Copilot On Front Seat 90 0 kg 198 5 Ibs Acro Fuel 51 L 37 0 kg 81 5 lbs 101 L Fuel In Wing Tanks 73 0 kg 160 9 Ibs Aircraft Empty Weight 660 0 kg 1455 Ibs 950 0 kg 2094 4 Ibs To find C G follow line Pilot Rear Seat from Empty Weight to 90 kg 198 5 165 Point 1 Continue on line Copilot Front Seat to 90 kg Point 7 Now follow line Fuel via Point 8 51 L 13 5 US gal Acro Fuel to Point 9 101 L 26 6 US gal Fuel in Wing Tank FIND Weight 950 kg 2094 4 lbs C G 75 4 cm 29 6 inch 6 3 2 Weight and Balance Record Sheet WEIGHT MOMENT EMPTY WEIGHT PILOT COPILOT ACRO FUEL WING FUEL Xw E WxX gt w Page Date 31 March 2009 6 7 Section 6 Pilot s Operating Handbook Weight and Balance and Equipment List EXTRA 6 4 LOADING WEIGHTS AND MOMENTS OCCUPANTS max 2 WEIGHT PILOT COPILOT Pilot REAR SEAT FRONT SEAT Parachute Arm 207cm 81 5 inch Arm 98 cm 38 4 inch INxLBS MOMENT INxLBS 10758 5068 11654 5491 12551 5913 13447 6336 14344 6758 15240 7180 16137 7603 FUEL MAX 171 LITER 45 1 US GAL ACRO amp CENTER TANK WING TANK LITER KG x CM 65 143 10 26 360 313 144 31 8 20 5 3 721 629 180 39 7 40 10 6 1442 1257 2
19. Paragraph 914 1 914 1 1 914 1 2 914 1 3 914 2 914 3 914 3 1 914 4 914 5 SECTION 914 GARMIN GTX 327 TRANSPONDER Table of Contents Page GENERAL 914 3 Mode Selection Keys eet aet 914 3 Gode ein 914 4 Keys forother GTX 327 914 4 LIMITATIONS 914 5 EMERGENCY PROCEDUBRES 914 6 IMPORTANT COGS E 914 6 NORMAL 5 1 914 6 PERFORMANCE 914 6 Page Date 15 December 2005 914 1 Section 914 Pilot s Operating Handbook GARMIN GTX 327Transponder XTRA EXTRA 300L Left blank intentionally 914 2 Page Date 15 December 2005 Pilot s Operating Handbook Section 914 EXTRA 300L GARMIN GTX 327 Transponder 914 1 GENERAL The GARMIN GTX 327 is a panel mounted TSO d transponder with the addition of timing functions Thetransponderis a radio transmitter and receiver that operates on radar frequencies receiving ground radar interrogations at 1030 MHz and transmitting a coded response of pulses to ground based radar on a frequency of 1090 MHz TONG FLIGHT TINE 01 23 20 mmm LSTOP NOTE The GTX327 owner accepts all responsibility for obtaining the proper license before using the transponder The coverage you can
20. 2 8 Aircraft Identity 2 8 Operating Placards eC M 2 9 Instr ment 214446 2 12 KINDS OF OPERATION EQUIPMENT LIST 2 13 NOISE LEVEL 2 14 Page Date 20 April 2002 2 4 Section 2 Pilot s Operating Handbook Limitations XTRA EXTRA 300L Left blank intentionally 2 2 Page Date 20 April 2002 Pilot s Operating Handbook Section 2 EXTRA 300L lt XTRA Limitations SECTION 2 LIMITATIONS 2 1 GENERAL This section includes operating limitations instrument markings and basic placards necessary for the safe operation of the aircraft its engine standard systems and standard equipment The limitations included in this section have been approved by the EASA Observance of these operating limitations is required by national aviation regulations NOTE In case of an aircraft equipped with specific options additional information required for safe operation will be contained in Section 9 Supplements Instrument markings and placards are provided for the acrobatic category only for normal category refer to corresponding limitations This aircraft is certified under Type Certification Data Sheet T C D S EASA A 362 Any exceedance of give
21. 55914 0008 esini e duex3 pue dn 10 15 ssal 1 141 18n 810 ql 7602 096 suollipuoo 2 gt e o Ov 06 0 OL 0c oe 9 1 pis no 0 921 9 Page Date 19 April 2012 Section 921 Lycoming AEIO 580 B1A Engine XTRA Pilot s Operating Handbook EXTRA 300L 921 5 4 Cruise Performance Chart Configuration 2 Configuration T O Weight Acro amp Center Tank Fuel Capacity Total Fuel Capacity 950 kg 2095 Ib 69 L 18 2 US gal 1891 49 9 US gal Range and Endurance values include fuel for warm up and Take Off from SL max cont Power climb to cruising altitude and a reserve of 21 L 5 55 US gal for 45 minutes with 45 Power 2 L 0 53 US gal unusable fuel is taken into account At ISA Conditions PA Eng Manif PowerSetting Fuel TAS IAS Endur Range Mixture Press Consumption m rpm inHg hp L h gal h kts km h kts km h h nm km Best 2000 2700 26 5 91 286 88 2 23 3 182 6 338 173 320 1 73 317 587 Power 610 2400 24 0 71 225 687 182 167 6 310 160 296 2 22 373 691 Power 2200 23 2 62 195 50 5 13 3 159 3 295 152 282 3 03 481 891 Economy 2000 22 5 52 165 426 11 3 1502 278
22. 906 4 906 7 DESCRIPTION AND OPERATION OF THE SYSTEM 906 4 906 8 HANDLING SERVICING AND MAINTENANGCE 906 6 Page Date 20 April 2002 906 1 Section 906 junii Pilot s Operating Handbook Digital RPM Indicator XTRA EXTRA 300L Left blank intentionally 906 2 Page Date 20 April 2002 Pilot s Operating Handbook Section 906 EXTRA 300L XTRA Digital RPM Indicator 906 DIGITAL RPMINDICATOR 906 1 GENERAL The EXTRA 300 L can be equipped with the optional P 1000 Digital RPM indicator as an alternative to the mechanical VDO RPM indicator One of the following models is used P100 230 635 00 max 2600RPM P100 230 643 00 max 2700RPM 906 2 LIMITATIONS The operation limitations are not affected by the installation of the P 1000 Digital RPM indicator The model of digital RPM indicator installed must match the applicable RPM limitation approved for the propeller installed Refer to the applicable noise level limitation included in section 2 or within any relevant supplement The face ofthe indicator is placarded with the unchanged engine RPM operating range Additionally the operating RPM ranges are indicated on the large green yellow and red LEDs These LEDs are located on the upper right corner of the indicator face Model P100 230 635 00 max 2600RPM 2600 906 3 EM
23. 918 5 EMERGENCY PROCEDURES cec rire reote cei utere 918 5 Important TE 918 5 NORMAL PROCEDURES uu a isa 918 6 ase leli t 918 6 Page Date 15 December 2005 918 1 Section 918 mE Pilot s Operating Handbook BECKER ATC 2000 Transponder XTRA EXTRA 300L Left blank intentionally 918 2 Page Date 15 December 2005 Pilot s Operating Handbook Section 918 EXTRA 300L BECKER 2000 Transponder 918 1 GENERAL The Becker panel mounted ATC 2000 Transponderis a radio transmitter and receiver that fulfills the role of the airborne beacon equipment according to the requirements of the Air Traffic Radar Beacon System ATCRBS Its functionality includes replying to ATCRBS Mode A and Mode C interrogations It operates on radar frequencies receiving ground radar interrogations at 1030 MHz and transmitting a coded response of pulses to ground based radar on a frequency of 1090 MHz The 2000 equipped with IDENT capability that activates the Special Position Identification SPI pulse REPLY lamp Code readout IDENT button First digit A Second B Third digit C Fourth digit D Coding switch Mode switch Coding switch Controls Description Function OFF SBY ON ALT TEST Four Position rotary switch OFF Transponder is switched off mode switch and on
24. 150 278 3 02 487 902 1 3 284 263 264 246 2200 237 65 195 50 5 902 Economy 2000 23 0 55 165 42 6 153 1 284 142 263 3 56 544 1007 Economy 2000 19 7 45 185 36 5 9 6 142 6 264 133 246 418 591 1095 Economy 6000 2700 23 6 83 248 77 6 20 5 180 5 334 162 300 1 97 351 650 Power 1829 2500 23 3 75 225 69 8 18 4 174 3 323 158 293 2 19 377 698 Power 2200 232 65 195 50 5 13 3 165 6 307 149 276 3 00 493 913 Economy 2000 22 5 55 165 42 6 11 3 156 1 289 141 261 3 54 531 983 Economy 2000 19 3 45 135 36 5 9 6 145 4 269 131 243 4 442 598 1107 Economy 8000 2700 21 8 77 231 73 4 179 5 332 156 289 2 08 367 680 Power 2438 2675 21 5 75 225 71 9 177 8 829 155 287 2 12 371 687 Power 2350 21 5 65 195 52 0 169 0 813 147 272 2 90 485 898 Economy 2050 21 4 55 165 43 0 159 3 295 139 257 3 49 552 1022 Economy 275 241 2000 18 8 45 135 36 5 9 6 148 4 130 4 10 604 1119 10000 2700 20 2 72 215 69 6 18 4 178 5 331 151 280 2 19 382 707 Power 3048 2500 19 9 65 195 53 6 14 2 172 4 319 148 274 2 81 476 882 Economy 2150 19 9 55 165 43 7 11 5 162 5 301 138 256 3 42 549 1017 Economy 2000 184 45 185 36 5 9 6 151 4 280 1
25. 1886 2514 3144 8771 Apart from the improved performance the engine is equipped on the left side with a retard type magneto This magneto has a retard breaker providing a fixed retard and long duration boosted spark for starting A Slick Start System completes the installation Page Date 19 April 2012 921 13 Section 921 Pilot s Operating Handbook Lycoming AEIO 580 B1A Engine XTRA EXTRA 300L Configuration 1 Configuration 2 Figure 921 1 Center Tank Versions 921 14 Page Date 19 April 2012 Pilot s Operating Handbook Section 921 EXTRA 300L XTRA Lycoming AEIO 580 B1A Engine Figure 921 1 shows both fuselage fuel tank configurations which are available for the EXTRA 300L ex factory Item 6 shows the contour of the center tank with 42 L 11 1 US gal capacity configuration 1 Item 7 shows the contour of the center tank with 60 L 15 9 US gal capacity configuration 2 In each configuration the center tanks are located above the acro tank 1 having 91 2 4 US gal fuel quantity They are installed in the same place and in the same manner This includes the vent line 2 and the fuel filler 5 location However the steel tubes of the fuselage carryingthe 60 tank and 15 mounting have been reinforced The configuration 1 fuel quantity probe 3 is located in front of the fuel filler 5 the configuration 2 probe 4 is located behind The fuel quanti
26. 913 3 Front Panel 913 3 System EE 913 5 Error Reporting Fault 913 7 LIMITATIONS 2 aS 913 8 EMERGENCY PROCEDURES 913 8 NORMAL PROCEDURES 913 8 azizelll bie 913 8 Page Date 15 December 2005 913 1 Section 913 mE Pilot s Operating Handbook FILSER TRT 800 Transponder XTRA EXTRA 300L Left blank intentionally 913 2 Page Date 15 December 2005 Pilot s Operating Handbook 2 Section 913 EXTRA 300L XTRA FILSER TRT 800 Transponder 913 1 GENERAL The TRT 800 is Level 2es Class2 SSR Mode S Elementary and Enhanced Surveillance Transponder It has Mode A Mode A C and Mode S capability In Mode S the transponder provides acquisition and extended squitter capability Furthermore the TRT 800 has a built in barometric pressure altitude coder in 100 ft increments NOTE Refer to latest edition of Filser TRT 800 Pilot s Operation Manual Doc No 03 210 010 11 to get familiar with the TRT 800 Transponder The following illustration of the front panel of the TRT 800 will assist the operator to understand this Mode S Transponder Display or sat On Off Flight Di FID Rotating for 1000 Rotating for 1 Sguitter flag elimina Activa
27. Max sump capacity 16 qts Min sump capacity 9 qts For temperatures and oil grades refer to Section 1 7 7 10 3 1 The engine is supported by four shock mounts type LORD or BARRY CONTROLS to the tig welded steel tube engine mount which is attached to the fuselage with four bolts on the firewall axis The engine cowling is divided into two parts a lower and an upper part both made of glass fibre carbonfibre reinforced epoxy The parts are fixed by a number of screws and the upper cowling has a separate hatch for easy access to the oil dip stick 7 10 4 PROPELLER The standard propeller is a 3 blade wood composite constant speed propeller type MTV 9 B C C200 15 The propeller has a diameter of 2 0 m A 4 blade propeller type MTV 14 B C C190 17 with a diameter of 1 9 m is also available as an optional equippment 7 10 5 THROTTLE Dual control cub type mounted on the left side of the cockpit Page Date 15 December 2005 7 11 Section 7 Pilot s Operating Handbook Description and Operation of Aircraft and Systems lt s X TRA EXTRA 300L 7 10 6 MIXTURE Vernier control located at the left side of the rear cockpit red knob 7107 RPM CONTROL Vernier control on the left side of the rear cockpit Preselection of RPM possible due to constant speed governor blue knob 7 10 8 FUEL SELECTOR VALVE Dual control A rotary fuel selector valve is mounted behind the firewall on th
28. Section 902 Pilot s Operating Handbook Electric Pedal Adjustment XTRA EXTRA 300L attachment A full travel from the most rearward to the most forward position takes approxi mately 15sec ZOO OOS So QOO 990999 TT Q CIRCUITBREAKER 7 5A 7 5A 902 8 HANDLING SERVICING AND MAINTENANCE Not affected 902 4 Page Date 8 October 2009 s s i Handbook XTR A SECTION 903 ELECTRONIC ACCELEROMETER Table of Contents Paragraph Page 903 1 GENERAL uuu uD nu Su u as 903 3 903 2 LIMITATIONS 903 3 903 3 EMERGENCY PROCEDURES 903 3 903 4 NORMAL PROCEDURES ueni 903 3 903 5 dsiuellnUIed 903 3 903 6 WEIGHT AND BALANCE dan avita 903 3 903 7 DESCRIPTION AND OPERATION OF THE SYSTEM 903 3 903 8 HANDLING SERVICING AND MAINTENANCE 4 4 4444 12211 903 9 Page Date 20 April 2002 903 1 Section 903 Pilot s Operating Handbook Electronic Accelerometer XTRA EXTRA 300L Left blank intentionally 903 2 Page Date 20 April 2002 Pilot s Operating Handbook Section 903 EXTRA 300L X TR
29. at any time inversion stops in this case 9 A VFR code that was preset in this way can be activated as described in chapter VFR Code Activation 10 Atimeout for inversion 10 sec is introduced if no action happens Nothing stored as long as F is not pressed NOTE It is possible to leave the setting procedure with SEL button G at any time and normal mode is available then Indication SEL on the display changes backto mode indication If STO button F was not used no change has been stored 920 1 8 FLIGHT OPERATION IN MODE A C S REPLY CODE AND ALTITUDE CODE 1 When ATC requests the transmission squawk switch the transponder to ALT using mode switch A NOTE In exceptions the altitude has to be turned off i e switch the transponder to ON using mode switch A 2 The transponder replies using the selected Code and in response to mode C interrogation it transmits the altitude of the aircraft to A R onthe left next to the Code on the display signals the transponder replies NOTE Switch the transponder to Stand by SBY if the Code has to be changed Otherwise if could happen that a Code with a special meaning see chapter K e g highjack will be transmitted and unwanted actions could take place Page Date 31 March 2009 920 9 Section 920 Pilot s Operating Handbook BECKER BXP 6401 Transponder XTRA EXTRA 300L 920 1 9 VFR CODE ACTIVATION 1 Press the VFR push button J The pre
30. 1 Section 925 junii Pilot s Operating Handbook GARMIN GNC 420W XTRA EXTRA 300L Left blank intentionally 925 2 Page Date 31 March 2009 Pilot s Operating Handbook Section 925 EXTRA 300L XTRA GARMIN GNC 420W 925 1 GENERAL The Garmin GNC 420W GPS Navigator is a panel mounted unit that contains a GPS receiver for GPS navigation plus VHF Com radio inan integrated unit with a moving map and color display The GNC 420W features a graphical display which may also be used to depict terrain data This supplementis written for main software version 3 00 and GPS software version 3 0 andis not suitable for earlier software versions Some differences in operation may be observed when comparing the information in this supplement to later software versions Verify the information herein with the 400W Series Pilot s Guide amp Reference P N 190 00356 00 applicable Revision you received with your unit There you will also find further information Photocell Freq Graphic Moving Comm rroq Window Map Display and Direct To Key Nav Freq inafi Flip Flop Window Navigation Info Range Keys Menu Key Power and Com Bm Clear Key Volume Squelch Data Can ds P Enter Key i BB WE Function and Nav Radio 30 r X I Page Number Volume e am Nav Radio Large Knob Flip Flop Large Knob Small Knob Com VLOC p
31. 2000 20 2 45 135 36 5 9 139 9 259 134 248 4 52 632 1171 Economy 4000 2700 25 4 89 267 82 7 21 8 181 5 336 168 311 2 00 361 668 Power 1219 2400 24 6 75 225 68 7 18 2 170 9 317 158 293 2 40 409 757 Power 2200 23 7 65 195 50 5 13 3 162 4 301 150 278 3 26 527 977 Economy 2000 23 0 55 165 42 6 11 3 158 1 284 142 263 3 86 589 1091 Economy 2000 19 7 45 135 36 5 9 6 142 6 264 133 246 4 52 640 1185 Economy 6000 2700 23 6 83 249 77 6 1829 2500 23 3 75 225 69 8 2200 23 2 65 195 50 5 2000 22 5 55 165 42 6 2000 19 3 45 135 36 5 9 180 5 334 162 300 2 13 380 704 Power 1743 323 158 293 2 37 408 755 Power 165 6 307 149 276 3 24 533 988 Economy 156 1 289 141 261 3 84 597 1105 Economy 145 4 269 131 243 4 46 647 1199 Economy 8000 2700 21 8 77 231 73 4 179 5 332 156 289 2 25 397 736 Power 2438 2675 21 5 75 225 719 177 8 829 155 287 2 29 402 745 Power 2350 21 5 65 195 52 0 169 0 313 147 272 3 14 526 973 Economy 2050 21 4 55 165 43 0 159 3 295 139 257 3 78 598 1107 Economy 287 241 2000 18 8 45 135 36 5 9 6 148 4 130 4 44 655 1213 Economy 10000 2700 20 2 72 216 69 6 18 4 178 5 331 151 280 2 37 414 767 Power 3048 2500 19 9 65 195 53 6 14 2 172 4
32. INFORMATION MANUAL EXTRA 300L MANUFACTURER EXTRA Flugzeugproduktions und Vertriebs GmbH Flugplatz Dinslaken 46569 H nxe Federal Republic of Germany WARNING This is an Information Manual and may be used for general purposes only This Information Manual is not kept current It must not be used as a substitute for the official FAA EASA Approved Pilot s Operating Handbook required for operation of the airplane Left blank intentionally Pilot s Operating Handbook EXTRA 300L XTRA LOG OF REVISIONS Dates of issue for original and revised pages Original 9 September 1994 Revision No 1 26 June 1997 Revision No 2 7 June 1999 Edition No 2 20 April 2002 Rev No 1 2nd Ed 15 December 2005 Rev No 2 2nd Ed 20 September 2006 Rev No 2nd Ed 6 June 2008 Rev No 4 2nd Ed 5 December 2008 Rev No 5 2nd Ed 16 March 2009 Rev No 6 2nd Ed 31 March 2009 Rev No 7 2nd Ed 08 October 2009 Rev 8 2nd Ed 19 April 2012 Rev No 9 2nd Ed 17 January 2013 Rev No 10 2nd Ed 31 October 2013 Date and sign of approval LBA approved 31 January 1995 LBAapproved 27 August 1997 LBAapproved 23
33. Pilot s Operating Handbook Electronic Accelerometer lt XTRA EXTRA 300L The other output display are twentyfive LEDs which are arranged in a semicircle The upper twelve LEDs show positive acceleration the lower twelve LEDs show negative acceleration The middle LED is on line all time long INSTANTANEOUS ACCELERATION The current value of acceleration is called Instantaneous Acceleration It is shown by the LED display if the value is between 12g and 129 the Instantaneous Acceleration is zero g only the middle LED lights up Every single g illuminates one more LED in positive up or negative down direction For example The Instantaneous Acceleration is 5g the middle LED and five LEDs in positive direction are illuminated If the Instantaneous Acceleration is 7g the middle LED and seven LEDs in negative direction are illuminated In case the absolute value of the Instantaneous Acceleration is greater then 12g all twelve LEDs of this range are turned on CURRENT EXTREME VALUES A A permanent illumination of two LEDs one for positive acceleration and another one for negative acceleration shows the Current Extreme Values They are signed by two illumi nated LEDs one in the positive and one in the negative range These two Current Extreme Values are shown furthermore on the LC Display in case of normal operation the positive Current Extreme Value is shown in the upper line and the negative Current Extreme
34. Section 926 EXTRA 300L XTRA ARTEX ME 406 ELT 926 1 GENERAL To improve the passive security the EXTRA 300 L can be equipped with an optional Emergency Locator Transmitter ARTEX ME 406 Inthe eventof acrash the ME 406 activates automatically automatic fixed AF configuration and transmits the standard swepttone on 121 5 MHz lasting until battery poweris gone This 121 5 MHz signalis mainly used to pinpointthe beacon during search and rescue operations In addition for the first 24 hours of operation a 406 MHz signal is transmitted at 50 second intervals This transmission lasts 440 ms and contains identification data programmed into the beacon and is received by Cospas Sarsat satellites Thetransmitted data is referenced in a database maintained bythe national authority responsible for ELT registration and usedto identifythe beacon and owner When the ELT is activated the buzzer beeps and the panel LED pulses periodically The time between pulses lengthen after a predetermined transmitter on time NOTE In October 2000 the International Cospas Sarsat Program announced at its 25th Council Session held in London UK that it plans to terminate satellite processing of distress signals from 121 5 and 243 MHz emergency beacons on February 1 2009 Accuracy Doppler positioning is employed using both 121 5 MHz and 406 MHz signals Position accuracy ofthe 121 5 MHz signalis within an area of approximately 15 20 km rad
35. number of the aircraft The pilot has to change the FID manually if necessary 912 1 3 ERROR REPORTING FAULT CODES Thetransponder s reception transmission altitude and power supply are monitored periodically This self testing routine is permanently active in the background If any error occurs due to an internal malfunction or from an external disturbance at the antenna the transponder changes to the Stanby mode and Error is displayed on the lowest line Additionally the result of the internal analysis are displayed in the second line LIST OF POSSIBLE ERRORS 1 ANT will appear if the antenna is defective e g broken cable 2 FLerr instead of the altitude appears on the display if there is an error with the altimeter or if the aircraft is outside the altitude range FL 010 to FL350 If the mode ACS was active before it will change to mode A S automatically 3 DC for a faulty transmitter power supply 4 FPG for internal communication errors 5 will appear for transmitter error In this case the unit will change to STBY and will stop all transmission Page Date 15 December 2005 912 7 Section 912 Pilot s Operating Handbook FILSER TRT 600 Transponder XTRA EXTRA 300L To meet ICAO specifications the TRT 600 uses an external memory inside the aircraft connector housing of the cable set which is a part of the aircraft Because this cable is installed permanent into the aircra
36. 109 109 0 gal h 35gal h 35 h Page Date 19 April 2012 Pilot s Operating Handbook Pilot s Operating Handbook Section 2 EXTRA 300L lt XTRA Limitations MANIFOLD PRESSURE INDICATOR green arc 10 25 Hg yellow arc 25 Hg 29 5 Hg red radial 29 5 Hg 2 15 KINDS OF OPERATION EQUIPMENT LIST The aircraft may be operated in day VFR when the appropriate equipment is installed and operable Flying under icing conditions is prohibited The following equipment list identifies the systems and equipment upon which type certification for each kind of operation was predicated The following systems and items of equipment must be installed and operable for the particular kind of operation indicated NORMAL ACROBATIC seat 2 seats COMMUNICATION 1 Transceiver VHF 1 1 1 ELECTRICAL POWER 1 Battery 1 1 1 2 Alternator 1 1 1 3 Ammeter 1 1 1 FLIGHT CONTROL SYSTEM 1 Elevator trim control 1 1 1 2 Stall warning 1 1 1 FUEL 1 Boost pump 1 1 1 2 Fuel quantity indicator 2 2 2 3 Manifold pressure 1 1 1 4 Fuel flow indicator 1 1 1 5 Fuel pressure 0 0 0 LIGHT 1 Wing tip position strobe light 1 1 1 NAVIGATION 1 Altimeter 1 1 1 2 Airspeed indicator 1 1 1 3 Mag direction indicator 1 1 1 4 OAT indicator 0 0 0 5 Vertical speed indicator 0 0 0 6 Turn and bank indicator 0 0 0 7 Artificial horizon 0 0 0 8 Directional gyro 0 0 0 9 Transponder 1 1 1 1 In so
37. 153 1 284 142 263 3 06 467 865 Economy 2000 190 43 135 36 5 9 6 142 6 264 133 246 3 59 507 939 Economy 6000 2700 228 79 248 77 6 20 5 180 5 334 162 300 1 69 301 557 Power 1829 2500 22 2 71 225 69 8 18 4 174 3 323 156 289 1 88 323 598 Power 2200 22 2 62 195 50 5 13 3 165 6 307 149 276 2 57 422 782 Economy 2000 21 5 52 165 42 6 11 3 156 1 289 141 261 3 04 472 874 Economy 2000 185 43 135 365 9 6 145 4 269 131 243 3 53 512 948 Economy 8000 2700 21 0 73 231 73 4 19 4 179 6 333 166 307 1 79 314 582 Power 2438 2675 20 7 71 225 71 9 19 0 177 8 329 156 289 1 82 318 589 Power 2350 206 62 195 52 0 13 7 169 0 313 147 272 2 49 415 769 Economy 2050 20 6 52 165 43 0 11 4 159 3 295 139 257 299 472 874 Economy 10000 2700 19 8 69 215 69 6 18 4 178 6 331 151 280 1 88 327 606 Power 3048 2500 19 2 62 195 53 6 14 2 172 4 319 146 270 2 41 407 754 Economy 2150 19 3 52 165 437 11 5 162 5 301 138 256 2 93 469 869 Economy 1 For temperatures above below Standard ISA increase decrease Range 1 7 and Endurance 1 1 for each 10 C 18 F above below Standard Day Temperature for particular altitude 2 Best Power or Best Economy see latest issue of Textron Lycoming AEIO 580 B1A Ope
38. 7 6 Page Date 20 April 2002 Pilot s Operating Handbook EXTRA 300L XTRA Section 7 Description and Operation of Aircraft and Systems Standard Optional Position ltem X X X X X X X X x x x x x x x x NOTE Magneto Selector switch amp starter Amperemeter Airspeed indicator Magn Direction indicator Oil pressure Oil temperature EGT CHT COM RPM indicator Circuit breaker g meter Manifold pressure Fuel Flow Altimeter Master switch Fuel Quantity Acro Tank Fuel Quantity Wing Tank Vertical speed indicator Turn and bank indicator Artificial horizon Fuel pressure Intercom button Directional gyro RPM control Prop governor Mixture control Throttle lever Stick Radio button Fuel shutoff valve Trim lever and indicator Boost pump This list may be modified by the minimum equipment requirements of individual certifying authorities Page Date 20 April 2002 Section 7 Pilot s Operating Handbook Description and Operation of Aircraft and Systems lt s X TRA EXTRA 300L 7 6 2 INSTRUMENT PANEL FRONT COCKPIT Normally the instument panel in the front cockpit is only equipped with the following positions 3 Airspeed indicator 12 Altimeter indicator 20 Intercom button 24 Throttle 25 Stick 26 Radio button 27 Fuel shutoff valve 7 7 LANDING GEAR The landing gear is a composite construction with a multichamber fiberglass
39. 9ec lt 959 ver TZS ove 688 SOL cov OST 610 erc Qu Qu SL GIOS Uu SL I 0 L SL Vd 40701 050 4 98 206 do 89 9 02 408 201 86 Do 0 Jdo 1 2901 LYO EE 541 2 4 ose AONVLSIC 4 Page Date 16 March 2009 908 6 Pilot s Operating Handbook Section 908 EXTRA 300L XTRA Airtow Hook CLIMBRATE Conditions Power 2500 Rpm and full throttle mixture rich Speed of the aircraft tow 76 KIAS 140 Km h Weight of the towing aircraft m 820 Kg 1808 Ib 1 Pilot 86 kg Acro amp Center Tank full 38 L Wingtank 30 L Tow force glider with m 350 kg 772 Ibs PA 0 329 10 i 1000 305 2000 610 3000 914 4000 1219 5000 1524 6000 1829 7000 2134 8000 2438 Tow force glider with 600 kg 1323 165 PA 0 32 F OAT 10 50 F 20 C e 1 1000 305 2000 610 3000 914 4000 1219 5000 1524 6000 1829 7000 2134 8000 2438 0 C 32 F OAT 10 C 50 F 20 C 68 F 30 C 86 F SL 1000 305 2000 610 3000 914 4000 1219 5000 1524 6000 1829 7000 2134 8000 2438 Page Date 16 March 2009 908 7 Section 908 Pilot s Operating Handbook Airtow Hook XTRA EXTRA 300L 9086 WEIGHT AND BALANCE Not affected 908 7 DESCRIPTION OF THE SYSTEM The releas
40. Brakes SECURE 80 KIAS 148 km h FLY OVER noting terrain and obstructions then reaching a safe altitude and airspeed OFF SLIGHTLY TAIL LOW OFF IDLE CUT OFF OFF Pull amp Turn APPLY HEAVILY Page Date 16 March 2009 Section 3 Emergency Procedures Pilot s Operating Handbook EXTRA 3001 3 4 FIRES 3 4 1 DURING START ON GROUND 1 Cranking 2 Fuel shutoff valve 3 Power 4 Engine 5 After engine stop 6 Fire CONTINUE to get a start which would suck the flames and accumulated fuel through the air inlet and into the engine OFF Pull amp Turn 1700 RPM for one minute SHUT DOWN ABANDON aircraft and inspect for damage EXTINGUISH using fire extinguisher if available Do not open engine compartment access doors while engine is on fire 3 4 2 IF ENGINE FAILS TO START 1 Cranking 2 Throttle 3 Mixture 4 Fuel shutoff valve If fire is extinguished 5 Master switch 6 Ignition switch 7 Engine compartment CONTINUE FULL OPEN IDLE CUT OFF OFF Pull amp Turn OFF OFF INSPECT Page Date 20 April 2002 Pilot s Operating Handbook Section 3 EXTRA 300L XTRA Emergency Procedures 3 4 3 ENGINE FIRE IN FLIGHT 1 Mixture IDLE CUT OFF 2 Fuel shutoff valve OFF Pull amp Turn 3 Master switch OFF 4 Airspeed 100 KIAS 185 km h find your airspeed attitude which will keep the fire away from
41. Exchange squawk coda STET 5 5 standby to active 912 1 1 FRONT PANEL OPERATION The input elements consist of four rotating knobs and five push buttons Page Date 15 December 2005 912 3 Section 912 Pilot s Operating Handbook FILSER TRT 600 Transponder XTRA EXTRA 300L ROTATING KNOBS Four rotating knobs are used to select the IDENT CODE The assignments X X X X indicate the position of the code number set by each knob PUSH BUTTONS ON OFF The unit can be turned on by pressing the ON OFF button for less then 1 second The unit can be turned off by pressing the ON OFF button for more then 2 seconds also refer to the System Operation Paragraph 912 1 2 MODE The following modes can be selected in sequence by pressing the MODE button STBY Standby Mode used for aircraft on ground with reduced squitter rate only Mode S with altitude reporting all ZERO only A S Mode A active with Mode C frames only and Mode S with altitude reporting all ZERO only ACS Mode and 5 full active ARROWS UP AND DOWN To activate the inserted SQUAWK CODE fromthe lower standby line to the upper active position the button with the UP AND DOWN ARROWS shall be pressed IDENT The IDENT push button causes the special position identification pulse SPI to be transmitted for a period of 18 seconds FID In the Standby Mode the Aircraft Identification Flight Identification and Aircraft Ad
42. June 1999 LBAapproved 30 October 2002 EASA Approval EASA A A 01101 Date of Approval 20 December 2005 EASA Approval EASA A A 01319 Date of Approval 20 November 2006 EASA Approval EASA A C 08351 Date of Approval 24 July 2008 EASA Approval EASA A C 10781 Date of Approval 18 February 2009 Approved under the authority of DOA N EASA 21J 073 ECO AM 300 09 07 Date of Approval 6 April 2009 EASA Approval 10026766 Date of Approval 7 August 2009 Approved under the authority of DOA N EASA 21J 073 FAA Validation Process TDO306CE A P EASA CSV A 01467 Date of Approval 14 October 2009 Approved under the authority of DOA N EASA 21J 073 ANAC Validation Process EASA Project N 001001 1276 Date of Approval 08 October 2012 Approved under the authority of DOA N EASA 21J 073 ECO AM 300 12 13 Date of Approval 04 March 2013 Approved under the authority of DOA N EASA 21J 073 ANAC Validation Process amp ECO 300 12 13 AM 300 13 03 AM 300 13 08 Date of Approval 14 November 2013 Page Date 31 October 2013 XTRA Pilot s Operating Handbook EXTRA 300L LOGOFEFFECTIVE PAGES Page Date Page Date 31 March 2009 6 10
43. The barometric pressure is set to standard pressure of 29 92 in Hg or 1013 mB Table 1 Knob Sync Operation 924 7 8 HOTKEY OPERATION During normal operations the five line select soft keys on the lower right side ofthe display bezel are referred to as Hot Keys Hot Keys provide single action access to frequently used functions An electronic legend adjacent to each Hot Key indicates its hot key function When the legend is green the function is active When itis gray the function is inactive The legend always annunciates the current state TAPES Hot Key 1 enables disables the display of the airspeed and altitude tapes MINIMUMS Hot Key 2 enables disables the display of the Minimums 924 8 Page Date 31 March 2009 Pilot s Operating Handbook Section 924 EXTRA 300L XTRA ASPEN EFD1000 PILOT PFD COMPASS PRESENTATION FORMAT Hot Key 3 toggles the compass between a 360 rose display and a 100 deg ARC display BASEMAP AND DECLUTTER LEVEL Hot Key 4 is used to enable the basemap and control the amount of basemap symbology that is presented to the pilot Each successive push ofthe MAP hotkey will change the basemap declutter level in a round robin sequence Available selections are FP ONLY and OFF The FP ONLY selection displays just the flight plan legs and waypoints associated with the GPS flight plan and no other basemap features OFF removes all basemap and flight plan symbology GPSSTE
44. U 2 3 ice 2 3 aU E 2 4 Engine LUMMMATIOMNS e E TREE 2 4 PROPELLER m 2 5 ple 2 5 WEIGHT AND ENVELOPE I R sasa 2 5 Normal FIIghluk aa 2 5 Acrobatic Flight 1 Seat uuu ai tene Yn aha 2 5 Acrobatic 2 5 2 6 ACROBATIC MANEUVERS J J J J JJ 2 6 Normal u R 2 6 2 6 LOAD FACTOR cR 2 7 Non al Flight uk aaa 2 7 uyu EE 2 8 FLIGHT CREW LIMITS 2 8 KINDS OF OPERATIONAL LIMITS 2 2 2 os ete etna nne nani 2 8 Structural Temperature Colour 2 8 MAXIMUM OPERATING 2 8 TIRE PRESSURE ic ua Sau H 2 8 MARKINGS AND PLACARDS u u u uuu
45. Value is shown in the lower line They are both signed by an A as first character of every line The Current Extreme Values change if the Instantaneous Acceleration is greater than the last positive or lower than the last negative Current Extreme Value the positive or the negative The Current Extreme Values can be reset to Og by pushing the buttons TOTAL EXTREME VALUE B Eventhough the two Current Extreme Values are reset to Og there will remain a positive and a negative Total Extreme Value in the memory As soon as a Current Extreme Value occurs that is greater than the positive or lower than the negative Total Extreme Value the corresponding Total Extreme Value is exchanged with the Current Extreme Value This is a possibility to store the positive and the negative Total Extreme Value during different actions while the Current Extreme Values are reseted to 09 after every single action The Total Extreme Values be shown or reseted to 00 by pushing the buttons They signed with a B as the first character on every LC Display line The Total Extreme Values only change if one of them is lower than the corresponding Current Extreme Value or if they are reset to Og Here is an example Since the last reset of the Current Extreme Values and the Total Extreme Values the maximum of the positive acceleration was 90 and the maximum of the negative acceleration was 5g The Inst
46. connector mustbein place for the G switch to activate the unit The jumperis installed onthe mating half of the connector so that when the connector is installed the beaconis armed This allows the beacon to be handled or shipped without nuisance activation front connector removed NOTE The ELT can still be manually activated using the local switch on the front of the ELT Care should be taken when transporting or shipping the ELT not to move the switch or allow packing material to become lodged such as to toggle the switch 926 7 2 SELF TEST MODE Upon turn off from back to state the ELT automatically enters a self test mode that transmits a 406 MHz test coded transmission that monitors certain system functions before returning to the ARM mode The transmission is ignored by any satellite that receives this signal but the ELT requires it to check output power and correct frequency Ifthe ELT is left activated for approximately 50 seconds or more adistress signal generated that is accepted by the satellites In addition to 121 5 and 406 MHz signal integrity other operating parameters are checked during the self test Error codes are then generated if other problems are found The error codes are displayed by a series of blinks of the ELT LED remote LED and audio indicator See Installed Transmitter Test section for more details and a description of the error codes NOTE Any time the
47. ile the wor ile the wor OVERHEAT RISK OVERHEAT RISK INDICATOR appears flying INDICATOR appears flying EXTRA is prohibited EXTRA is prohibited The standard aircraft is designed to operate within a range of ambient air temperature from 20 C to 44 C 4 F to 114 F at sea level It is possible to start the engine using the aircraft battery at 20 C 4 F without preheating Below 10 14 F OAT a special oil breather line must be adapted available as kit 7 2 FUSELAGE The fuselage structure consists of a steel tube construction integrating the wing and empennage connections as well as the seats The fuselage except the rear lower part is faired with an aramid carbon laminate shell Within the exhaust area stainless steel sheet metal is used The upper fuselage body surface is one part from firewall to vertical stabilizer including the correlated canopy frame Only the lower rear part of the fuselage is covered with Ceconite 102 The canopy frame itself is constructed by carbon laminate The canopy is one part opens to the right and is held in the open position by a belt Emergency jettisonning is achieved by Page Date 31 March 2009 7 3 Section 7 Pilot s Operating Handbook Description and Operation of Aircraft and Systems lt X TRA EXTRA 300L simply unlatching the canopy For additional pilot protection a roll bar is installed behind the rear pilots seat 7 3 WINGS The wing is of CRP
48. navigation equipment as appropriate 925 4 Page Date 31 March 2009 Pilot s Operating Handbook 2 Section 925 EXTRA 300L XTRA GARMIN GNC 420W LOSS OF INTEGRITY MONITORING If Loss of Integrity Monitoring message is displayed revert to an alternate means of navigation appropriate to the route and phase of flight or periodically cross checkthe GPS guidance to other approved means of navigation SEARCHING A NEARBY AIRPORT To select a nearby airport as a direct to waypoint 1 Press the direct to key The select direct to waypoint page will appear with the waypoint identifierfield highlighted 2 the large right knob to highlight the nearest airport NRST field 3 Turn the small right knob to display a window showing up to nine nearby airports 4 Continue turning the small right knob to scroll through the list and highlight the desired airport 5 Press ENT to confirm the selected airport and ENT to activate the direct to function 9254 NORMAL PROCEDURES TO ACTIVATE AN EXISTING FLIGHT PLAN 1 Press FPL and turn the small right knob to display the flight plan catalog 2 Press the small right knob to activate the cursor 3 Turn the large right knob to highlight the desired flight plan and press MENU to display the flight plan catalog options 4 Turn the large right knob to highlight Activate Flight Plan and press ENT 5 Press and hold the CLR key to open the default NAV page 925 5 PERFORMAN
49. 144 267 3 59 538 996 Economy 2000 19 4 43 135 365 9 6 139 9 259 134 248 4 18 584 1082 Economy 4000 2700 24 5 85 267 827 21 9 181 5 336 168 311 1 85 333 617 Power 1219 2400 23 4 71 225 68 7 18 2 1709 317 158 293 2 22 378 700 Power 2200 22 7 62 195 50 5 13 3 162 4 301 150 278 3 02 487 902 Economy 2000 21 8 52 165 42 6 11 3 153 1 284 142 263 3 57 544 1007 Economy 2000 19 0 43 135 365 96 1426 264 133 246 4 18 591 1095 Economy 6000 2700 22 8 79 248 77 6 20 5 1805 334 162 300 1 97 351 650 Power 1829 2500 222 71 225 698 18 4 1743 323 156 289 2 19 377 698 Power 2200 222 62 195 50 5 13 3 165 6 307 149 276 3 00 493 913 Economy 2000 21 5 52 165 426 11 3 156 1 289 141 261 3 55 551 1020 Economy 2000 18 5 43 135 365 96 145 4 269 131 243 4 12 598 1107 Economy 8000 2700 21 0 73 231 73 4 19 4 179 6 333 166 307 2 08 367 680 Power 2438 2675 20 7 71 225 719 19 0 177 8 329 156 289 2 12 371 687 Power 2350 20 6 62 195 52 0 13 7 169 0 313 147 272 2 90 485 898 Economy 2050 20 6 52 165 43 0 11 4 159 3 295 139 257 3 49 552 1022 Economy 10000 2700 19 8 69 215 696 18 4 178 6 331 151 280 2 19 382 707 Power 3048 2500 192 62 195 536 14 2 1724 319 146 270 2 81 476
50. 161 6 F the word RISK appears and flying is prohibited STRUCTURAL CAUTION OVERHEAT While the word RISK INDICATOR appears flying EXTRA is prohibited 2 12 MAXIMUM OPERATING ALTITUDE Max certified operating altitude is 16000 ft MSL 4877 m 2 13 TIRE PRESSURE The tire pressure is 3 4 Bar 49 3 PSI 2 14 MARKINGS AND PLACARDS 2141 AIRCRAFTIDENTITY PLACARDS OMANUFACTURER 9 o EXTRA EXTRA FLUGZEUGBAU GMBH FLUGZEUGPRODUKTIONS MODEL EA 300 L UND VERTRIEBS GMBH SERIAL NUMBER MODEL EA 300 L oTC NUMBER o SERIAL NUMBER O TC NUMBER A67EU 2 8 Page Date 20 September 2006 Pilot s Operating Handbook Section 2 EXTRA 300L lt s XTRA Limitations 2 142 OPERATING PLACARDS V 158 KTS V 293 km h ACRO indi Ve 140 KTS NORMAL O 259 km h NORMAL near airspeed indicator THE MARKINGS AND PLACARDSINSTALLEDIN in the rear cockpit THIS AIRPLANE CONTAIN OPERATING LIMITATIONS WHICH MUST BE COMPLIED WITH WHEN OPERATING THIS AIRPLANE IN THE ACROBATIC CATEGORY OTHER LIMITATIONS WHICH MUST BE COMPLIED WITH WHEN OPERATING THIS AIRPLANE IN THIS CATEGORY OR IN THE NORMAL CATEGORY ARE CONTAINED IN THE AIRPLANE FLIGHT MANUAL APPLICABLE RPM LIMITATION MUST BE OBSERVED THIS AIRPLANE IS CERTIFICATED on the rear instrument panel FOR VFR DAY OPERATION OPERATION IN KNOWN ICING CONDITIONS IS PROHIBITED FUEL near each filler cap AVGAS 100 100 LL WI
51. 2 US gal Usable fuel capacity for acrobatic 671 17 7 US gal C Fuel pressure at inlet to fuel injector Max 448 2kPa 65psig Min 200 0kPa 29psig Min Idle 82 7kPa 12psig d Cylinder head temperature Max 241 C 465 Page Date 8 October 2009 921 3 Section 921 Pilot s Operating Handbook Lycoming AEIO 580 B1A Engine XTRA EXTRA 921 2 2 Weight Limits Max allowed empty weight Normal category configuration 1 742 kg 1636 Ib configuration 2 729 kg 1607 Ib Acrobatic category single seat operation ACRO I configuration 1 698 kg 1540 Ib configuration 2 686 kg 1512 Ib double seat operation ACRO II 662 kg 1460 Ib double seat operation ACRO III 742 kg 1436 Ib 921 2 3 Propeller Limitations TheMTV 9 B C C 198 25 propeller may be operated only with the AEIO 580 B1 A engine With respect to the noise level refer to paragraph 921 2 5 following rotational speed limitations apply forthe MTV 9 B C C 198 25 propeller MaximumTake Off and Maximum Continuous 2600 RPM NOTE RPM limitation due to compliance with applicable noise protection requirements ICAO Annex 16 and FAR 36 However for non US registered airplanes an enhanced rotational speed limitation of 2700 RPM may be permissable when registered in the Acrobatic Category only as ICAO Annex 16 grants an exception for airplanes specially designed for acrobatic purposes 921 2 4 Operating Placards T
52. 2002 911 3 endete 31 March 2009 5 Tthru 5 2 20 April 2002 iir 20 April 2002 5 3 thru 5 4 16 March 2009 912 1 thru912 8 15 December 2005 BD 20 April 2002 913 1 thru 913 8 15 December 2005 5 6 thru 5 9 16 March 2009 914 1 thru914 6 15 December 2005 5 10 5 12 20 April 2002 915 1 thru915 2 15 December 2005 uc hana 31 March 2009 915 3 thru915 4 5 December 2008 BATA 16 March 2009 915 5 E 15 December 2005 67062 ance 20 April 2002 915 D iiec 5 December 2008 OB 20 September 2006 915 7thru915 8 15 December 2005 31 2009 916 1 thru 916 2 15 December 2005 6 5 thru 6 6 20 April 2002 916 9 cort retro tract 31 March 2009 GT 31 March 2009 916 4thru 916 6 15 December 2005 6 8 thru 6 9 20 April 2002 917 1 thru917 8 31 March 2009 Page Date 31 October 2013 Pilot s Operating Handbook XIRA EXTRA 300L Page Date 918 1 thru 918 6 15 December 2005 919 1 thru 919 8 15 December 2005 920 1 thru 920 10 31 March 2009 92151 19 2012 921 2 5 December 2008 921
53. 5 5 T a 4 3 2 1 60 40 20 0 20 40 60 TEMPERATURE Page Date 20 April 2002 5 5 5 5 3 AIRSPEED CALIBRATION CAS km h 110 130 150 170 190 210 230 250 270 290 310 330 350 370 390 210 390 200 370 190 350 180 330 170 310 160 290 150 UD 270 lt 140 250 130 F 120 110 210 100 1 90 170 80 150 70 130 60 110 60 80 100 120 140 160 180 200 KCAS NOTE Indicated airspeed assumes zero instrument error 5 6 Page Date 16 March 2009 Pilot s Operating Handbook Section 5 EXTRA 300L Performance 5 4 STALLSPEED CONDITION POWER IDLE FORWARD C G STALL SPEEDS ANGLE OF BANK WEIGHT CATEGORY 0 30 45 19 1 159 1 419 kg Ibs KIAS km h KIAS km h KIAS km h 950 Normal 60 65 72 2095 111 120 133 870 ACRO 2 seat 57 61 68 1918 106 113 126 820 ACRO 1 seat 55 59 65 1808 102 109 120 Max altitude loss during stall recovery is approximately 100 ft 30 m Page Date 16 March 2009 5 Section 5 Pilot s Operating Handbook Performance XTRA EXTRA 300L 5 5 TAKE OFF PERFORMANCE Power T O Power Runway Concrete NOTE For every 5 kts 9 km h headwind the T O distance can be decreased by 4 For every 3 6 km h tailwind
54. 71 L 150 30 0 51 m 5 49 ft left right 30 tolerance 29 Page Date 19 April 2012 Pilot s Operating Handbook Section 1 EXTRA 300L XTRA General 1 4 ENGINE Manufacturer Textron Lycoming Williamsport Plant PA 17701 USA Type Lycoming AEIO 540 L1B5 b TypeLycoming AEIO 540 L1B5D Rated power 300 HP 2700 RPM 270 HP 2400 RPM 1 5 PROPELLER Manufacturer MT Propeller Entwicklung GmbH Federal Republic of Germany 8 TypeMTV 9 B C C 200 15 3 blade constant speed b TypeMTV 14 B C C 190 17 4 constant speed 1 5 1 EXHAUST SYSTEMS OPTIONAL Manufacturer Gomolzig Flugzeug und Maschinenbau GmbH Federal Republic of Germany Exhaust Silencer for standard system PN EA 300 NSD GO3 606500 Complete 6 in 1 System with integrated Silencer PN EA300 606000 1 6 FUEL Fuel type AVGAS 100 100 LL for alternate fuel grades see later issues of Textron Lycoming S I No 1070 Minimum 100 130 octane Maximum 115 145 octane Total fuel capacity 171L 45 1 US gal Wingtanks 2 x 60 L 120L 31 7US gal Acro amp center tank 511 13 4US gal Usable fuel capacity in the system 165 5L 43 7US gal Usable fuel capacity for acrobatic 45 5L 12 0US gal 1 7 OIL Maximum sump capacity 16 US qt Minimum sump capacity 9 US qt Alltemperatures SAE 15W50 or 20W50 gt 27 80 60 gt 16 60 SAE 40 or 60 1 C til 32 C SAE 40 30 F 90 F Page Date 31 March 200
55. KIAS and the input voltage is below 12 5 0 3 V the EFD will automatically switch to its internal battery e g aircraft charging system failure The EFD1000 PILOT PFD internal battery will provide at least 30 minutes of power when itis fully charged The battery provides power to the display head and the RSM with the emergency GPS Reducing the backlight intensity will extend the battery operating time Battery charge status may be viewed from the Power Settings page of the Main Menu See Section 924 7 13 for more information NOTES As a protection mechanism the EFD1000 PILOT PFD internal battery may not charge when the battery temperature is at extreme high or low temperatures This situation may occur when the battery was being used and system power is subsequently restored or it may occur under high or low ambient temperatures If operation from the internal battery occurs during night and or IFR operations one should land as soon as possible even if external power is restored as the battery will not recharge following restoration of external power until the battery temperature has returned to normal Aunitoperating from battery may be powered off using the Shut Down command available in the Power Settings Menu Page Date 31 March 2009 924 5 Section 924 Pilot s Operating Handbook ASPENEFD1000PILOT PFD XTRA EXTRA In the unlikely event that the normal power control is not working the EF
56. LOW RPM lt PROP gt HIGH RPM on RPM control unit in the rear cockpit LEAN lt MIXTURE gt RICH mixture control unit in the rear cockpit CLOSE lt THROTTLE gt near throttle control in both cockpits LOCK lt lt gt UNLOCK near canopy locking handles of each cockpit nearthe eyeball type adjustable vents 2 10 Page Date 15 December 2005 Pilot s Operating Handbook EXTRA 300L XTRA Section 2 Limitations Approved acrobatic maneuvers recommended entry airspeeds Maneuvers Airspeeds min KIAS maxKIAS Segment Horizontal Line 45 climbing 90 up 45 diving 90 diving 1 4 Loop climb Loop Stall turn Maneuvers Airspeeds min km h maxkm h Horizontal Line 45 climbing 90 up 45 diving 90 diving 1 4 Loop climb Loop Stall turn CAUTION Maneuvers Airspeeds min KIAS maxKIAS Aileron roll Snap roll Tail slide Spin Inverted spin flight Less than 4 edge Less than 10 5 Maneuvers Airspeeds min km h maxkm h Aileron roll Snap roll Tail slide Spin Inverted spin Inverted flight Lessthan 4min Knife edge Less than 10 5 Particular caution must exercised when performing maneuvers speeds above 158 KIAS Large abrupt control inputs above this speed may impose unacceptably high loads which exce
57. Meter L Litres US gal US liquid gallon 3 79 litres US qt US liquid quart 0 946 litres hp Horse power english h Hour kts Knots nm h 1 852 kilometer per hour km h Kilometer per hour lbs English pound 0 4536 kg hPa hekto Pascal inHg Inches of mercury MP Manifold pressure PA Pressure altitude ft nm Nautical miles 1 852 km rom Revolutions per minute CG Center of gravity Arm Arm is the horizontal distance from reference datum Moment is the product of weight of an item multiplied by its arm Page Date 31 March 2009 1 7 EXTRA 300L Pilot s Operating Handbook XTRA Section 1 General CONVERSION TABLE 1 11 10 00 cN 0 5 CO 00 s SE SE LOO O O TIN sr Lo CO LO LO LO LO LO LO HY NY sf LO LO r lt lt
58. Pilot s Operating Handbook Airtow Hook XTRA EXTRA 3001 Left blank intentionally 908 2 Page Date 20 April 2002 Pilot s Operating Handbook Section 908 EXTRA 300L XTRA Airtow Hook 908 1 GENERAL The EXTRA 300 L can optionally be equipped with a TOST glider air tow release Typ E 85 The release mechanism is mounted at the tail spring end and actuated from the cockpit by a yellow knob 908 2 LIMITATIONS The following combinations are certified Aircraft a Engine AEIO 540 L1B5 or AEIO 540 L1B5D Propeller MTV 14 B C C190 17 Exhaust system Typ Gomolzig EA 300 606000 or standard exhaust PC 63104 with silencer NSD GO3 606500 b Engine AEIO 580 B1A Propeller MTV 9 B C C 198 25 restricted to max 2600 RPM or MTV 14 B C C 190 17 Exhaust system Typ Gomolzig EA 300 606000 Air tow release system according to replacement instruction UA 300 4 95 Air tow release TOST E 85 Glider MTOW ofthe glider 765Kg 1687 105 Max air towing speed of the glider 152 km h or above Air tow cable and breaking piece weak links Length of the synthetic tow between 40 m 130 ft and 60 m 195 ft Ultimate load of the air tow max 850 kp 1875 Ibs If tows with higher ultimate load are used a breaking piece weak links of max 850 kp 1875 lbs must be interconnected For a safe air towing the following points must be observed Max Takeoff Weight 820 kg 1813 Ibs 870 kg 1924 Ibs Max Empty W
59. Provided it was the right code the LC Display shows the current time and date with a cursor under the first digit By pushing S2 you can change the digit The change can be confirmed by pushing S1 In this case the cursor moves to the next digit The instrument changes into the Normal Operating Mode if you have stepped through all digits with the cursor or you waited more than six seconds without pushing a button In this case the time and date on the display are transferred into the clock If you try to enter an impossible number like 18 as months or 35 as days the instrument turns back 903 8 Page Date 20 April 2002 Pilot s Operating Handbook 2 Section 903 EXTRA 300L X TRA Electronic Accelerometer into the Normal Operating Mode and the clock will be programmed with the correct changed numbers The wrongly changed number is exchanged by its old value 903 8 HANDLING SERVICING AND MAINTENANCE If the absolute extreme value C indicates that the operating limits have been exceeded the manufacturer must be informed The battery inside which is used for the clock power supply backup is expected to have a lifetime of 5 to 10 years A weak battery can be exchanged by the manufacturer only Page Date 20 April 2002 903 9 Section 903 Pilot s Operating Handbook Electronic Accelerometer XTRA EXTRA 300L Left blank intentionally 903 10 Page Date 20 April 2002 2 Handbook XTR A
60. Temp Ind 1 Oil Press Westach 3DA3 3MM 0 14 1 62 A Oil Temp Ind 3 1 8 or 3DA3 3KV 1 Oil Temp Sender Westach W399 S9 0 08 0 11 A 1 Oil Press Sensor Mediamate 387 100MM 0 12 0 04 A or 387 100KV 1 Oil Press Westach 2DA3 3MM 0 09 1 62 A Oil Temp Ind 2 1 4 or 2DA3 3KV 1 Oil Temp Sender Westach W399 S9 0 08 0 11 A 1 Oil Press Sensor Mediamate 387 100MM 0 12 0 04 A or 387 100KV 1 Oil Press Oil Temp Ind UMA D2 OP130U 0 09 1 62 A 2 1 4 OT300U 01 1 Oil Temp Probe UMA 1B3A 0 08 0 11 A 1 Oil Press Sender UMA N1EU150G A or 0 12 0 04 A T1EU150G A 1 Stall Sensor EXTRA 73106 1 0 07 0 53 R 1 Stall Warning Horn EMAG EM S 110P 0 13 1 60 R 1 Accelerometer EXTRA DSA 12 0 37 1 60 1 Accelerometer Kollsman or Pioneer AN5745 0 40 1 60 O or Bendix or Jaeger or Century 1 Accelerometer EZE Technologies DA 55 0 16 1 60 O 1 ELT and Antenna Pointer 3000 10 0 90 2 60 O 1 ELT System ARTEX ME 406 1 42 2 60 A 1 Turn amp Bank Ind United Instruments 9501 2 TSO C3b 0 55 1 63 1 Turn amp Bank Ind Castleberry C101 TSO C101T 0 55 1 63 1 Horizon electric digital RC Allen RCA 2600 2 0 tilt 0 24 1 63 1 Horizon electric digital RC Allen RCA 2600 2 0 tilt 0 13 1 61 A 102 0202 01 1 Horizon electric digital RC Allen RCA 2600 3 0 tilt 0 45 1 63 1 Horizon electric digital RC Allen RCA 2600 3 0 tilt 0 19 1 61 A 102 0203 01 1 Slip Indicator RC Allen 444 0010 01 0 03 1 63 A on RCA 2600 1 Altimeter front United
61. Wings empennage and landing gear are manufactured of composite material The aircraft is a two seater with the rear seat instrumented for pilot in comand 1 1 SPECIFICATION OF CLASS The aircraft is certified in normal and acrobatic category T C D S EASA A 362 1 2 MANUFACTURER EXTRA Flugzeugproduktions und Vertriebs GmbH Flugplatz Dinslaken 46569 H nxe Federal Republic of Germany 1 3 TECHNICAL DATA 1 3 1 3 VIEW DRAWING Page Date 31 March 2009 1 3 Section 1 General XTRA Pilot s Operating Handbook EXTRA 1 3 2 MAINDATA Length Height Span Wheel base Wheel track 1 3 3 WING Wing span Wing area Airfoil Chord MAC Aileron area Aileron deflection 1 3 4 HORIZONTAL TAIL Span Area Airfoil 1 3 5 ELEVATOR Area Elevator deflection Trim tab deflection 1 3 6 VERTICAL TAIL Area Airfoil 1 3 7 RUDDER Area Rudder deflection 6 96 m 22 83 ft 2 62 m 8 60 ft 8 00 m 26 25 ft 5 07 m 16 63 ft 1 80 m 5 91 ft 8 0 m 26 25 ft 10 7 m 115 17 ft Root MA 15 S Tip MA 12 S Root 1 85 m Tip 0 88 m 1 404 m 4 61 ft 2 x 0 855 m 2 x 9 20 ft up down 30 tolerance 2 3 20 m 10 50 ft 2 56 m 27 56 ft Wortmann FX71 L 150 30 0 77 m 8 29 ft up down 25 tolerance 2 up 40 down 50 tolerance 5 1 39 m 14 96 ft Wortmann FX
62. are illuminated during the submenues 4 DISPLAY OF THE TOTAL EXTREME VALUES Push button twice S1 Reset of the Total Extreme Values Push button twice S1 and once S2 you push S1 twice the LC Display shows the Total extreme values These values are the maximums of positive and negative acceleration that occurred since the last reset of these values They are signed with a B as first charac ter of a line like the following example B 84g B 4 29 In case you want to reset these two values you have to press 52 and the instrument sets the Total Extreme Values to 0g and returns into the Normal Operating Mode Provided you pushed 51 instead of S2 the LC Display will show the Absolute Extreme Values If there is no button pushed the instrument will return into the Normal Operating Mode 5 DISPLAY OF THE ABSOLUTE EXTREME VALUES push button three times S1 Display of time and date of the Absolute Extreme Values push button three times S1 and once S2 After pushing S1 for three times the LC Display shows the greatest positive and the greatest negative acceleration the instrument ever measured These two values are stored in the long term memory of the instrument and signed with a C as first character of the LC Display 9 69 C 83g Page Date 20 April 2002 903 7 Section 903 Pilot s Operating Handbook Electronic Accelerometer lt XTRA EXTRA 300L Additionally the long term me
63. at 1030 MHz and transmitting a coded response of pulses to ground based radar on a frequency of 1090 MHz The BXP 6401 is equipped with IDENT capability that activates the Special Position Identification SPI pulse NOTE The BXP 6401 owner accepts all responsibility for obtaining the proper license before using the transponder Refer to Becker Pilot s Guide Page Date 31 March 2009 920 3 Section 920 Pilot s Operating Handbook BECKER BXP 6401 Transponder XTRA EXTRA 300L 920 1 1 CONTROLS ANDINDICATORS A Mode Selector Rotary switch with 4 OFF position Transponder is switched off positions SBY position Standby mode is switched on ON position Mode A S is switched on Transmission of altitude information is suppressed ALT position Mode A C S is switched on and the altitude information is transmitted B Rotary switch Rotary optical encoder gt Rotary switch to change settings rotary mode of C 16 steps per turn C Button Push button Push to jump from digit to digit for settings or from mode of B one menu to the next generally used as an enter key D Push button Activates the Special Identifier SPI in ad dition to the reply code for approx 18 seconds during this time ID appears in the LC display E Display part 1 2 line LCD display Displays the following informations code indication in the top row flight level in the bottom row various informations
64. cockpit ambient temperature Page Date 31 March 2009 924 9 Section 924 Pilot s Operating Handbook ASPENEFD1000PILOT PFD XTRA EXTRA 924 7 10 MAPRANGE CONTROL The EFD1000 PILOT PFD basemap range may be to ranges of 2 5 5 10 15 20 30 40 60 80 100 and 200 nautical miles Map range is measured from the own ship position to the outside of the compass arc Toincreasethe range push the side ofthe range key located on the upper right side of the bezel To decrease the range push the side of the key The currently selected map range is displayed in the lower left corner of the display 924 7 11 DISPLAY REVERSION CONTROL AND ABNORMAL SHUTDOWN Single PFD installations do nothave adisplay reversion capability that can be activated by the REV button As such the reversion function is inoperative in single display installations In addition to display reversion control the REV button may be used to force the unit to power off should for example the display stop responding to pilot inputs When external power has been removed by pulling the PFD circuit breaker pressing and holding the REV button for 5 Seconds will produce in an immediate system shut down When external power is available PFD circuit breaker reset pressing and holding the REV button for 5 seconds will result in a system restart 924 7 12 WARNING CAUTION AND ADVISORY SUMMARY WARNINGS ONBAT 53 REM Red annun
65. display LOW POWER SUPPLY If the power supply to the transponder drops below 10 Volts the flag appears and starts flashing DISPLAYING AIRCRAFT ADDRESS AND FLIGHT IDENTIFICATION By pressing the FID button for less than 3 seconds while the unitis in Stanby Mode the left side of the bottom line will show the aircrafgt address NOTE Only authorized service station is allowed to enter or change the ICAO aircraft address If you do have the ICAO aircraft address Please refer to your national aviation authority to apply for your aircraft address 913 6 Page Date 15 December 2005 Pilot s Operating Handbook 2 Section 913 EXTRA 300L XTRA FILSER TRT 800 Transponder The Aircraft Identification FID code is displayed on the right bottom line and consists of seven alphanumerical characters CAUTION The ICAO Flight Plan specifies only 7 characters as Flight Identification Filser reserves 8 characters as stated in ED 73B for further expansion of the flight plan The user shall only program 7 characters for FID SELECTING FLIGHT IDENTIFICATION By pressing the button FID for more than 3 seconds the unit will change into the Flight Identification input menu This FID code is a changeable alphanumerical flight number The right lower knob is used to set the cursor position flashing and with the left lower knob the figures A Z blank and 0 9 can be selected To enter the code press the MODE butt
66. expect from the GTX 327 is limited to line of sight Low altitude or aircraft antenna shielding by the aircraft itself may result in reduced range Range can be improved by climbing to a higher altitude It may be possible to minimize antenna shielding by locating the antenna where dead spots are only noticed during abnormal flight attitudes CAUTION The GTX 327 should be turned off before starting or shutting down aircraft engine The GTX 327 Transponder is powered on by pressing the STBY ALT or ON keys or by the AVIONIC MASTER switch After power ona start up page will be displayed while the unit performs a self test 914 1 1 MODE SELECTION KEYS OFF Powers off the GTX 327 STBY Powers on the transponder in standby mode At power on the last active identification code will be selected When in standby mode the transponder will not reply to any interrogations ON Powers on the transponder in Mode A At power on the last active identification code will be selected Inthis mode the transponder replies to interrogations as indicated by the Reply Symbol Replies do not include altitude information ALT Powers on the transponder in Mode A and Mode C At power on the last active identification code will be selected In ALT mode the transponder replies to identification and altitude interrogations as indicated by the Reply Symbol Replies to altitude interrogations include standard pressure altitude received from a separate encoder
67. failure the screen displays 915 6 Page Date 5 December 2008 Pilot s Operating Handbook Section 915 EXTRA 300L XTRA GARMIN GTX 330 Transponder 915 2 LIMITATIONS Notapplicable 915 3 EMERGENCY PROCEDURES 915 3 1 IMPORTANT CODES 7600 Loss of communications 7500 Hijacking 7700 Emergency All secondary surveillance radar sites are ready to receive this code at all times See the Airman s Information Manual AIM for a detailed explanation of identification codes 915 4 NORMAL PROCEDURES Not applicable 915 5 PERFORMANCE Not applicable Page Date 15 December 2005 915 7 Section 915 mE Pilot s Operating Handbook GARMIN GTX 330 Transponder XTRA EXTRA 300L Left blank intentionally 915 8 Page Date 15 December 2005 Pilot s Operating Handbook TR A EXTRA 300L Paragraph 916 1 916 1 1 916 1 2 916 1 3 916 2 916 3 916 4 916 4 1 916 5 SECTION 916 BENDIX KING KT 76A TRANSPONDER Table of Contents Page GENERAL 916 3 Code Es reip 916 3 mE 916 4 Testing the KI AGA test ttt eer d cede c 916 4 LIMITATIONS cS 916 4 EMERGENCY PROCEDURE 916 4 NORMAL PROCEDURE cerae trente annon naa
68. in the bottom row additional indicators on the left side see Ref H 5 Push button Stores the selected values to the settings G SEL Push button Opens and selects the menu Display part 2 LCD indicators Displays additional indicators R for reply ID for Ident ALT for XPDR ALT mode or ON for XPDR ON mode FL for flight level J VFR Push button Activates VFR code in the upper row of the display 920 1 2 SWITCHING ON THEUNIT PRE FLIGHT CHECK 1 Checkthat the circuit breaker is set and switch on the aircraft power supply CAUTION Do not switch on the transponder if the motors or engines are being started or shut down 2 Using mode selector A switch the transponder from OFF to SBY A test then follows automatically for 1 seconds The display shows WAIT and the unit is subject to a self test simultaneously 3 After the switch on test has elapsed and no error message is written in the display the transponder switches to the mode set on the mode selector A 920 4 Page Date 31 March 2009 Pilot s Operating Handbook 2 Section 920 EXTRA 300L XTRA BECKER BXP 6401 Transponder NOTE The blind encoder is only powered if the transponder is not switched OFF at least SBY A blind encoder needs a warm up time sometimes a several minutes Therefore although the solid state transponder needs no warm up time turn the transponder to SBY immediately after starting the engine 920
69. normal polarity injects the smoke oil from the floptube smoke oil tank through an overpressure check valve and the injector nozzle into the hot exhaust gas to generate smoke The system consists of Main smoke oil tank with float switch Floptube smoke oil tank 909 6 Page Date 20 September 2006 Pilot s Operating Handbook Section 909 EXTRA 300L Smoke System Refill Injection pump in the pilot compartment with quick connector in the belly fairing Overpressure check valve in the smoke oil supply line to the nozzle Filter element in the refill line ON OFF switch on the throttle lever Tworelais changeover contact type for pump control SMOKE ARM switch to arm the system and SMOKE REFILL switch for refilling placed at the instrument panel Only 1 circuit breaker for pump and control placed at the instrument panel BE 5 CIRCUIT BREAKER BREAKER 909 8 HANDLING SERVICING AND MAINTENANCE At every refilling Check automatic shut off Additionally during the 100h Check for the DUAL PUMP SYSTEM Check the system for leakage lines fittings tanks Check the smoke oil tanks for proper attachment Check the function of the solenoid valve Clean the injector nozzle if required remove carbon debris Additionally during the 100h Check for the SINGLE PUMP SYSTEM Check the system for leakage lines fittings tanks Check t
70. not switch on the transponder if the motors or engines are being started or shut down 2 Using mode switch A switch the transponder from OFF to SBY Atestthen follows automatically for 3 seconds The display is flashing with all digits and the unit is subject to a self test simultaneously 919 4 Page Date 15 December 2005 Pilot s Operating Handbook nd Section 919 EXTRA 300L BECKER 4401 Transponder 3 After the switch on test has elapsed and no error message is written in the display the transponder switches to the mode set on the mode switch A Note The blind encoder is only powered if the transponder is not switched OFF at least SBY A blind encoder needs a warm up time sometimes a several minutes Therefore although the solid state transponder needs no warm up time turn the transponder to SBY immediately after starting the engine 919 1 3 SQUAWK SELECTION 1 The transponder remains switched in the standby mode until requested by the ground station ATC to transmit a code e g squawk alpha 6426 Using the double rotary switch B C set the 4 digit code requested by ATC as follows Using switch B move the cursor to the particular digit Digits 0 to 7 can then be set using switch C NOTES If switch B is turned clockwise or counter clockwise the cursor is moved one position to the right or the left The cursor appears only in the code display and is indicated by the flashi
71. procedure without storing push the SEL button G NOTE Aircraft Identifier Flight Number consists of max 7 characters on the left hand side oriented No dashes or spaces shall be included If the FN con sists of less than 7 characters the remaining characters on the right side shall be filled with spaces SWITCHING BACK TO DEFAULT 1 2 Press SEL button G to enter the select mode Rotate B to the indication First push on C indicates FN Al DEF inverted Can be set to AIZDEF with STO button CHANGING THE FLIGHT NUMBER Press SEL button G Rotate B until FN is displayed Push C twice to enter the FN editing mode Change the FN as described above 920 8 Page Date 31 March 2009 Pilot s Operating Handbook Section 920 EXTRA 300L XTRA BECKER BXP 6401 Transponder VFR CODE PRESETTING Press the SEL button G to get into configuration mode selection is indicated in the left bottom corner of the display under the operating mode indication 1 Rotate to the indication VFR XXXxX 2 First push to button C now left digit of the code is inverted 3 Now the digit can be changed with B 4 Second push to button C now next left digit of the code is inverted 5 The next digit can be changed with 6 and the same for next digits 7 Fifth push to button C now again first digit is inverted 8 Changes can be stored with STO button
72. proceed as follows Remove quick pins from the backrest adjustment and swivel the backrest forward to get access to the ELT unit Usethe unit master switch at the ELT unit analogously FUNCTION CHECK OF THEELT Ifthe aircraft receiver is operable listen on 121 5 MHz for ELT transmission Ensure thatthe antenna is clear of obstruction 926 4 NORMAL PROCEDURES Notaffected 926 5 PERFORMANCE Not affected 9266 WEIGHT amp CENTER OF GRAVITY Refer to the equipment list in Section 6 of this Handbook 926 4 Page Date 31 March 2009 Pilot s Operating Handbook Section 926 EXTRA 300L XTRA ARTEX ME 406 ELT 9267 SYSTEM DESCRIPTION The ELT installation consists of the ELT unit and a buzzer both fastened to the fuselage structure aft of the back seat an antenna located on the main fuselage cover behind the cockpit and a remote switch with LED indication located on the instrument panel The switch has the positions ARM and ON 926 7 1 SWITCH OPERATION Inacrash an acceleration activated crash sensor G switch turns the ELT on automatically when the ELT experiences a change in velocity or deceleration of 4 5 fps 0 5 fps Activation is also accomplished by means of the cockpit mounted remote switch or the switch on the ELT To deactivate the ELT set either switch to the ON position then back to ARM The ELT does not have an OFF position Instead a jumper between two pins on the front D sub
73. the Acrobatic Category only as ICAO Annex 16 grants an exception for airplanes specially designed for acrobatic purposes 2 6 WEIGHT LIMITS Max allowed empty weight Normal category 745 kg 1643lbs Acrobatic category 1 seat 701 kg 1546lbs 2 seats 665 kg 1466lbs Max allowed T O weight Normal category 950 kg 2095 165 Acrobatic category 1 seat 820 kg 1808 165 2 seats 870 kg 1918 Ibs Max allowed landing weight 950 kg 2095 Ibs 2 7 WEIGHT AND C G ENVELOPE Vertical reference fire wall Horizontal reference upper longerons in cockpit 2 7 1 NORMAL FLIGHT Max T O Weight forward C G rear C G 950 kg 2095 Ibs 67 1 cm 26 4 84 1 cm 33 1 below 2 7 2 ACROBATIC FLIGHT 1 SEAT Max T O Weight forward C G rear C G 820 kg 1808 165 67 1 cm 26 4 84 1 cm 33 1 below Page Date 8 October 2009 2 5 Section 2 Pilot s Operating Handbook Limitations XTRA EXTRA 300L 2 7 3 ACROBATIC FLIGHT 2 SEATS Max T O Weight forward C G rear C G 870 kg 1918 105 67 1 cm 26 4 84 1 cm 33 1 andbelow 2 8 ACROBATIC MANEUVERS 2 8 1 NORMAL FLIGHT All acrobatic maneuvers are prohibited except stall chandelle lazy eight and turns up to 60 degrees bank angle 2 8 2 ACROBATIC FLIGHT The plane is designed for unlimited acrobatics wing tank must be empty Inverted flight maneuvers are limited to max 4 min Recommended basic maneuver entry speeds are l
74. the cockpit 5 Land as soon as possible 3 5 ICING 3 5 1 INADVERTENT ICING ENCOUNTER 1 Turn back or change altitude to obtain an outside temperature that is less conductive to icing 2 Plan a landing at the nearest airfield With extremely rapid ice build up select a suitable off airport landing field 3 6 UNINTENTIONAL SPIN Refer to section 4 Normal Procedures acrobatic maneuver spin recovery 3 7 MANUAL BAIL OUT When in an emergency situation that requires abandoning the aircraft and while wearing a parachute which is at least strongly recommended for acrobatics Inform your passenger Reduce speed to 100 KIAS 185 km h if possible Pull mixture to lean Open canopy the low pressure over the canopy in normal flight will flip the canopy full open immediately Takeoff headset Open seat belt Leave airplane to the left side Try to avoid wing and tail Openparachute 5 Page Date 16 March 2009 3 7 Section 3 Pilot s Operating Handbook Emergency Procedures XTRA EXTRA 300L 3 8 EMERGENCY EXIT AFTER TURN OVER 1 Master switch OFF 2 Fuel shutoff valve OFF Pull amp Turn 3 Seat belts OPEN 4 Parachute harnesses if wearing aparachute OPEN 5 Canopy handle PULL TO OPEN NOTE If canopy fails to open break the canopy 6 Aircraft EVACUATE ASAP 3 9 ELEVATOR CONTROL FAILURE In case of elevator control failure the aircraft ca
75. the location and operation of the transmitter the following placards have to be attached in the aircraft placard outside on the left fuselage board in high of the ELT unit placard above the ELT circuit breaker see Fig 1 CIRCUIT BREAKER 1A Figure 1 Page Date 20 April 2002 904 3 Section 904 Pilot s Operating Handbook Emergency Locator Transmitter X TRA EXTRA 300L 904 3 EMERGENCY PROCEDURES Aircraft accident or forced landing Manual activation Warbling tone on headset 121 5 MHz Broken or disabled antenna Severed whip antenna cable Danger of fire in aircraft Temperature extreme in aircraft Poor transmitting location Short circuit in A C electric ves D Removal of ELT from A C 9 Pay attention for best transmission condition Stay close to the downed aircraft to permit easier spotting by airborne searchers Automatic and manual activation Although the ELT will be activated automatically by a ROLAMITE Type INTERTIA switch after an aircraft accident or forced landing with high G force turn additionally the remote switch optional in the rear panel or the unit master switch at the ELT unit to ON position The ELT will send a signal on the emergency frequencies of 121 5 MHz and 243 0 MHz B Control of the ELT If the aircraft receiver is operable listen on 121 5 MHz for ELT tran
76. 0 50 5 42 1 2 Sighting Dev LH RH EXTRA 83801 10 each 0 54 1 59 1 Aresti Card Holder EXTRA Assy 0 09 1 66 2 Wing Tie Down Rings EXTRA 83801 2 01 0 04 1 08 1 Remote Mounted Airwolf Filter Corp AFC K007 0 09 Oil Filter Kit 6 16 Page Date 31 October 2013 Pilot s Operating Handbook XTR A EXTRA 3001 Paragraph 7 1 7 2 7 3 7 4 7 5 7 5 1 7 5 2 7 5 8 7 5 4 7 5 5 7 6 7 6 1 7 6 2 7 7 7 8 7 9 7 10 7 10 1 7 10 2 7 10 3 7 10 4 7 10 5 7 10 6 7 10 7 7 10 8 7 10 9 7 11 7 12 7 13 SECTION7 DESCPRIPTION AND OPERATION OF AIRCRAFT AND SYSTEMS Table of Contents Page THE AIRGRAFT u l u 7 3 FUSELAGE m 7 3 luccpe 7 4 EMPENNAGE nene scis dieu eMe M Md III 7 4 FLIGHT CONTROL SYSTEM uuu 7 5 Primary Control SYSI8Im u aQ unn up A usss 7 5 Longitudinal Flight Control 7 5 Lateral Elight Control SySEem xiii tae eco rese oie aires 7 5 Directional Flight Control 7 5 secondary Control ERR ES 7 b INSTRUMENTAT O N uS 7 6 Instrument Panel Rear 1 7 6 Instrument Panel Front
77. 0 Military use Not enterable 915 4 Page Date 5 December 2008 Pilot s Operating Handbook Section 915 EXTRA 300L XTRA GARMIN GTX 330 Transponder Avoid selecting code 7500 and all codes in the 7600 7777 range These trigger special indicators in automated facilities Only the code 7500 will be decoded as the hijack code An aircraft s transponder code if available is utilized to enhance the tracking capabilities of the ATC facility therefore care should be taken when making routine code changes 915 1 3 KEYS FOR OTHER GTX 330 FUNCTIONS IDENT Pressing the IDENT key activates the Special Position Identification SPI Pulse for 18 seconds identifying your transponder return from others on the air traffic controller s screen The word IDENT will appear in the upper left corner of the display while the IDENT mode is active VFR Pressing the VFR key sets the transponder code to the pre programmed VFR code selected in the Configuration Mode Pressing the VFR key again will restore the previous identification code FUNC Pressing the FUNC key changes the page shown on the right side of the display Displayed data includes Pressure Altitude Flight Time Count Up timer Count Down timers In the Configuration Mode steps through function pages START STOP Starts and stops the Count Up Count Down and flight timers In the Configuration Mode steps through functions in reverse CRSR Initiates starting time entry fo
78. 0 Transponder 8 p 916 BENDIX KINGKT 76A Transponder 6 p 917 BENDIX KING KT 73 Transponder 8 p 918 BECKERATC2000 6 p 919 gt 4401 8 p 920 BECKER BXP 6401 Transponder essei 10 p 921 Lycoming AEIO 580 B1A 14 p 922 Center Tank Increased Capacity 8 p 923 GARMINGTX328 Transponder 8 p Page Date 5 December 2008 9 1 UM ume 924 ASPENEFD1000PILOT PED ainaani 12 925 QGARMINGNC420MW 8 926 8 927 AIRPLANES REGISTERED IN BRAZIL AND OPERATING UNDER THE AGENCIA NACIONAL DE AVIACAO CIVIL REQUIREMENTS 6 p 928 _EANDINGLIGHTLE
79. 01 126 00 latest revision for Instructions for Continued Airworthiness 924 12 Page Date 31 October 2013 Pilot s Operating Handbook x TRA EXTRA 300L Paragraph 925 1 925 1 1 925 1 2 925 2 925 2 1 925 3 925 3 1 925 3 2 925 4 925 5 925 6 925 7 925 7 1 925 7 2 SECTION 925 GARMIN GNC 420W Table of Contents Page GENERAL E 925 3 GPS WAAS TSO C146a Class 925 3 Class Oceanic Remote and other 925 3 B aperte 925 4 Placards oiin 925 4 EMERGENCY ABNORMAL PROCEDURES u U 925 4 Emergency Procedures u l m a 925 4 Abnormal rr err rk eaa e RARO P Eu E ERR RE I ka 925 4 NORMAL PROCEDURES rre Lo 925 5 PERFORMANCE 925 5 WEIGHT amp CENTER OF GRAVITY nnne nnne nn u u u u 925 6 SYSTEM DESCRIP TION 2 uuu Sasi sasa caia con nonc 925 6 Key and Knob Functions iiie i ii e Locus ti mee RIED 925 6 D fault Nav err eret e Rt x RR ERA 925 8 Page Date 31 March 2009 925
80. 01 6 901 7 STEERABLE TAIL WHEEL GENERAL To improve taxi and handling quality the EXTRA 300 L can be equipped with an optional steerable tailwheel The deflection angle of this tailwheel is arranged by the rudder control up to plus minus 30 Exceeding this deflection the tailwheel has a full swivel capability by a release mechanism LIMITATION The operation limitations are not effected due to the use of the steerable tailwheel EMERGENCY PROCEDURES There is no change of basic emergency procedures with the installation of the steerable tailwheel NORMAL PROCEDURES There are no changes for the described normal procedures after installation of the steerable tailwheel In addition to the existing normal procedures the light precompression of connec tor springs and movement of the rudder have to be checked during the preflight check PERFORMANCE Changes in flight performance due to installation of the steerable tailwheel are not notice able The given basic performance data under section 5 are still valid WEIGHT AND BALANCE A change of the running empty weight and resulting C G position after installation of the steerable tailwheel is neglectable because of minor differences in weight and C G between standard and optional steerable tailwheel DESCRIPTION OF THE SYSTEM The 5 inch tailwheel has a solid rubber tire and is rotatable by means of a wheelfork which is connected to a bearing steelsleeve This steelsleeve its
81. 1 EXTRA 300L Lycoming AEIO 580 B1A Engine 921 5 1 Cruise Performance Chart Configuration 1 Configuration T O Weight 950 kg 2095 Ib Center Tank Fuel Capacity Total Fuel Capacity 51 L 13 4 US gal 1711 45 2 US gal Range and Endurance values include fuel for warm up and Take Off from SL max cont Power climb to cruising altitude and a reserve of 21 L 5 55 US gal for 45 minutes with 45 Power 5 5 L 1 45 US gal unusable fuel is taken into account At ISA Conditions PA Eng Manif PowerSetting Fuel TAS IAS Endur Range Mixture Press Consumption 1 ft m rpm inHg e hp L h gal h kts km h km h h nm km Best 2000 2700 26 5 91 286 88 2 23 3 182 6 338 173 320 1 49 272 504 Power 610 2400 24 0 71 225 68 7 18 2 167 6 310 160 296 1 91 320 593 Power 2200 23 2 62 195 50 5 13 3 159 3 295 152 282 2 60 413 765 Economy 2000 22 5 52 165 42 6 11 3 150 2 278 144 267 3 08 462 856 Economy 2000 194 43 135 36 5 9 6 139 9 259 134 248 3 59 502 930 Economy 4000 2700 245 85 267 82 7 21 9 181 5 336 168 311 1 59 286 530 Power 1219 2400 23 4 71 225 68 7 18 2 170 9 317 158 293 1 91 324 600 Power 2200 22 7 62 195 50 5 13 3 162 4 301 150 278 2 59 418 774 Economy 2000 21 8 52 165 42 6 11 3
82. 1 2 7 Maximum Operating Altitude Maximum certified operating altitude is 10 000 ft MSL 3048 m 921 3 EMERGENCY PROCEDURES Not applicable 9214 NORMAL PROCEDURES Not applicable Page Date 19 April 2012 921 5 Section 921 Pilot s Operating Handbook Lycoming AEIO 580 B1A Engine EXTRA 3001 921 5 PERFORMANCE Due to the slightly increased power as well as the similar brake specific fuel consumption of the AEIO 580 B1A engine compared to the AEIO 540 L 1 B5 engine the performance data given in Section 5 of this handbook are considered to be conservative thus can be applied in general Even at 2600RPM the climb performance is slightly better than that of the aircraft equipped with the AEIO 540 L 185 engine The actual value ofthe climb rate at MTOW 950kg 2095165 SL ISA and T O power with 2600RPM is established as 2163ft min However the Cruise Performance Charts and related Drawings have been adapted with regard to the power settings The power settings are adjusted to match the absolute power values inthe HP column ofthe Cruise Performance Chart presented in Section 5 of this handbook For this reason the values of the power setting column deviate from the common values 75 65 etc Inthe Cruise Performance Chart for configuration 2 the increased fuel capacity of the center tank has been considered 921 6 Page Date 19 April 2012 Pilot s Operating Handbook XTRA Section 92
83. 1 3 DISPLAY Transponder s code is displayed in the top line using high readability font at all times in modes SBY ON ALT Depending on the configuration settings the Aircraft Identification or Flight Number FN is displayed in the bottom line Flight level is displayed in ALT mode in the bottom line of the display altitude FL x 100 in ft 920 1 4 SQUAWK SELECTION 1 The transponder remains switched in the standby mode until requested by the ground station ATC to transmit a code e g squawk alpha 6426 2 Using the rotary switch B and the button C set the 4 digit code requested by as follows a Using switch C move the cursor tothe particular digit Digits 0 to 7 can then be setusingthe rotary switch B NOTES Whilst settings are taking place the transmission branch of the transponder is inhibited to prevent unintentional transmission If only two digits were named by ATC e g Squawk alpha 64 then a zero is to be used for positions three and four i e 6400 b Thelastused codeis stored in each case andis also activated when the transponder is switched on IMPORTANT CODES 1200 The VFR code for any altitude in the US Refer to ICAO standards elsewhere 7000 The VFR code commonly used in Europe Refer to ICAO standards 0021 The VFR code commonly used in Germany default is set to 0021 at time of installation 7500 Hijack code Aircraft is subject to unlawful interference 7600 Loss of c
84. 1 6 476 60 15 9 3 2164 1886 252 55 6 80 21 1 6 127 0 2885 2514 28 8 63 5 100 26 4 0 158 8 3607 3144 324 71 4 120 31 7 A 190 5 4328 3771 36 7 80 9 6 8 Page Date 20 April 2002 Pilot s Operating Handbook Section 6 EXTRA 300L XTRA Weight and Balance and Equipment List 6 5 WEIGHTS AND MOMENTS LIMITS Weight kg Ibs 950 2095 900 1985 Max T O Cat Il 850 1918 Max T O A 800 1764 750 1653 700 1544 650 1432 62 66 70 74 78 82 86 Arm cm 24 4 25 9 27 5 29 1 30 7 32 2 33 8 inch Center of gravity cm inch Aft of the ref datum EXAMPLE At 790 KG 1741 LBS and 640000 kgcm the C G location is 80 0 cm 31 4 aft of ref datum Page Date 20 April 2002 6 9 Section 6 XTRA Pilot s Operating Handbook Weight and Balance and Equipment List EXTRA 3001 6 6 EQUIPMENT LIST EXTRA 3001 S N QTY ITEM MANUFACT PART OR P N WEIGHT MARKIF REQUIRED R kg m INSTALLED OPTIONAL O ALTERNAT A 1 Engine Textron Lycoming AEIO 540 L1B5 194 90 0 72 R R H ENPL RT9609 1 Magneto L H Slick 6251 or 6351 2 30 0 15 R 1 Magneto R H Slick 6250 or 6350 2 00 0 15 R 1 Engine Textron Lycoming AEIO 540 L1B5D 194 90 0 72 R H ENPL RT7471 1 Magnetos Bendix D6LN 3000 5 20 0 15 A 1 Engine Textron Lycoming AEIO 580 B1A 191 72 0 72 A R H ENPL
85. 20 3 30 1 03 A Front Seat 1011230 3x amp seat belts w ratchet 1113012 1 1x shoulder harness 1H3030 3 2x crotch strap 1CS924 D 1x 2 NAV STROBELTS Whelen A 600 PG PR 14 0 23 0 74 R 2 Power Supply Whelen A490T 0 54 0 74 R 1 Landing Light LED Whelen 01 71125 12 0 16 0 57 1 Standard Canopy EXTRA 26301 000 LV 13 50 1 69 R 1 Single Seat EXTRA 86411 011 LV 13 20 1 69 A Canopy 2 Electric Actuator SKF CARR 3 25 0 95 R Pedal Adjust 22x200x1 D12B 1 Long Range Tank EXTRA 86901 1 80 0 55 Page Date 31 October 2013 6 15 Section 6 XTRA Pilot s Operating Handbook Weight and Balance and Equipment List EXTRA 3001 QTY ITEM MANUFACT PART ORP N WEIGHT ARM MARKIF REQUIRED kg m INSTALLED OPTIONAL O ALTERNAT A 1 Center Tank 42 L EXTRA 66203 001 LK 3 30 0 30 R 1 Center Tank 60 L EXTRA 86713 010 LK 3 90 0 30 A 1 Fuel Selector Allen 6 S 122 0 19 0 73 R 1 Safety Cover EXTRA 86803 1 1 68 3 03 Polycarbonate 1 Dual Pump EXTRA 86100 8 80 0 16 Smoke System without Pumps 2 Smoke Oil Pump ITT Jabsco 8860 1203 3 60 0 10 Inject and Refill 2 Smoke Oil Pump ITT Jabsco 23620 3003 4 40 0 10 Inject and Refill 1 Smoke Oil Pump Johnson F3B 19 12V 2 00 0 05 Injection 1 Smoke Oil Pump Johnson F2P10 19 12V 1 65 0 25 Refill 1 Single Pump EXTRA 86112 9 20 0 30 Smoke System incl Pump Marco 12V 1 Airtow Hook EXTRA TOST 83607A0
86. 2002 910 1 Section 910 junii Pilot s Operating Handbook Acro Category XTRA EXTRA 300L Left blank intentionally 910 2 Page Date 20 April 2002 Pilot s Operating Handbook Section 910 EXTRA 300L XTRA Acro IIl Category 910 ACROIII CATEGORY 910 1 GENERAL The EXTRA 300 L can be operated in an additional two seat Acro III category This category is defined by MTOW of 950 kg 2095 Ibs a max load factor of 69 6g and a of 158 KIAS 293 km h 910 2 LIMITATIONS AIRSPEED Maneuver Speed Acro ll V 158 KIAS 293 km h WEIGHT LIMITS Max allowed empty weight 745 kg 1643 Ibs Max allowed T O weight 950 kg 2095 Ibs WEIGHT AND C G ENVELOPE Weight forward C G rear C G MTOW 950 kg 2095 Ibs and below 67 1 cm 26 4 84 1 cm 33 1 LOAD FACTOR 6g 6g for two seat occupied MTOW 950 kg 2095 Ibs OPERATING PLACARDS BERE near airspeed indicator VA 140 Kts Normal VA 259 km h Normal ACROBATIC 10 G 1 PILOT MTOW 820 KG 1808 LBS 8 G 2 PERSONS ON BOARD MTOW 870 KG 1918 LBS 6 G 2 PERSONS ON BOARD MTOW 950 KG 2095 LBS e MC E KEPE in both cockpits ACROBATICS INCL SPIN NOT APPROVED Page Date 16 March 2009 910 3 Section 910 Pilot s Operating Handbook Acro Category XTRA EXTRA 300L 910 3 EMERGENCY PROCEDURES Notaffe
87. 28G 10 70 0 23 R 1 Battery Concorde RG 25XC 10 40 0 23 A 1 Batt Charger Plug EXTRA 146 19 20 0 02 0 17 1 Ext Power Recept Div AN2552 3A 1 46 1 07 1 Ext Power Solenoid Switches Kidde 22735 0 40 0 03 1 Ext Power Solenoid White Rodgers 70 111 225 5 0 40 0 03 cont operation 1 Main Bus Solenoid White Rodgers 70 111 226 5 0 40 0 03 R 1 Starter Solenoid Switches Kidde 22735 0 40 0 03 R 1 Low Voltage Light OAK MS25041 2 0 02 1 63 R 1 Starter Engaged Light OAK MS25041 4 0 02 1 63 1 Ignition Switch 10 357200 1 0 15 1 63 R 2 Wheel Cleveland 40 151 4 00 0 33 R 2 Main Wheel Tires Div 5 00 5 6PR 3 90 0 33 R 1 Tail Wheel 5 EXTRA steerable 5 50 5 23 R 1 Tail Wheel 6 Assy Special Products 5 90 5 23 A Soft Aviation Inc 2 Brake Assy Cleveland 30 164 1 40 0 33 R 2 Brake Oyl front Cleveland 10 20 or 10 20E 0 55 0 15 R 2 Brake Oyl front Matco MC 4E 0 55 0 15 A 2 Brake Cyl rear Cleveland 10 20 or 10 20E 0 55 1 15 R 2 Brake Oyl rear Matco MC 4E 0 55 1 15 A 1 Brake Fluid Reservoir EXTRA 53301 1 0 20 0 03 R 1 Brake Fluid Reservoir ACS A 315 0 20 0 04 A 1 Safety Belt Assy Hooker 002 or FK0019 3 30 2 12 R Rear Seat 1011230 3x amp seat belts w ratchet 1113012 1 1x shoulder harness 1H5630 3 2x crotch strap 1CS924 D 1x 1 Safety Belt Assy Hooker 1011230 4x 2 90 1 03 R Front Seat 1H3030 3 2x seat belts 1CS924 D 1x shoulder harness crotch strap 1 Safety Belt Assy Hooker 004 or FK00
88. 29 239 4 07 611 1132 Economy 12000 2700 18 6 67 200 662 17 5 177 5 329 146 270 2 28 396 733 Power 3658 2675 184 65 195 55 3 14 9 176 0 326 144 267 2 71 467 865 Economy 2300 183 55 165 452 11 9 165 9 307 136 252 3 29 537 995 Economy 2000 17 9 45 185 36 5 9 6 154 5 286 127 235 403 617 1143 Economy 14000 2700 17 2 62 186 63 0 16 6 176 6 327 140 259 2 42 410 759 Power 4267 2450 17 0 55 165 46 7 12 3 169 4 314 135 250 3 17 524 970 Economy 2075 17 7 45 135 37 1 9 8 157 8 292 122 226 3 94 611 1132 Economy NOTE 1 Fortemperatures above below Standard ISA increase decrease Range 1 7 and Endurance 1 1 for each 10 C 18 F above below Standard Day Temperature for particular altitude Best Power or Best Economy see latest issue of Textron Lycoming Operator s Manual 4 10 Series AEIO 540 922 4 Page Date 16 March 2009 Section 922 Center Tank Increased Capacity Pilot s Operating Handbook EXTRA 300L XTRA 922 5 2 Range WN 00 lt 9 69 Dob 9 9 episjno 55914 1 0008 esini Jo 10 sn S S 7 12 Sse
89. 3 TRANSPONDER Table of Contents Paragraph Page 917 1 GENERAL 917 3 917 1 1 uuu 917 4 917 1 2 Code Selecto Me 917 4 917 1 3 Buttons selectors for other KT 73 Functions 917 5 917 1 4 Funcion Display 917 6 917 1 5 Programming 917 6 917 1 6 917 6 917 1 7 Failure Annunciato 917 7 917 2 LIMITATIONS 917 7 917 3 EMERGENCY PROCEDURES 917 7 917 4 NORMAL PROCEDURES 917 7 917 5 hi diaeQe H 917 7 Page Date 31 March 2009 917 1 Section 917 mE Pilot s Operating Handbook BENDIX KING KT 73 Transponder XTRA EXTRA 300L Left blank intentionally 917 2 Page Date 31 March 2009 Pilot s Operating Handbook Section 917 EXTRA 300L XTRA BENDIX KING KT 73 Transponder 917 1 GENERAL The BENDIX KING KT 73 panel mounted Mode S Transponder is radio transmitter and receiver that fulfills the role of the airborne beacon equipment according to the requirements of the Air Traffic Radar Beacon Sys
90. 319 148 274 3 04 516 956 Economy 2150 19 9 55 165 43 7 11 5 162 5 301 138 256 3 71 595 1103 Economy 2000 18 4 45 135 36 5 9 6 151 4 280 129 239 4 41 663 1228 Economy 12000 2700 18 6 67 201 66 2 17 5 177 5 829 146 270 2 47 429 795 Power 3658 2675 18 4 65 195 55 3 14 9 176 0 326 144 267 2 93 507 939 Economy 2300 18 3 55 165 45 2 11 9 165 9 307 136 252 3 56 583 1079 Economy 2000 17 9 45 185 36 5 9 6 154 5 286 127 235 4 37 670 1241 Economy 14000 2700 172 62 186 63 0 16 6 176 6 327 140 259 2 62 445 825 Power 4267 2450 17 0 55 165 46 7 12 3 169 4 314 135 250 3 44 569 1054 Economy 2075 17 7 45 185 37 1 9 8 157 8 292 122 226 4 28 665 1231 Economy NOTE 1 Fortemperatures above below Standard ISA increase decrease Range 1 796 and Endurance 1 1 for each 10 C 18 F above below Standard Day Temperature for particular altitude 2 Leaning with exhaust gas temperature EGT gauge For the adjustment Best Power first lean the mixture to achieve the top exhaust temperature and then enrich again until the exhaust temperature is 100 lower than peak EGT 907 4 Page Date 16 March 2009 Pilot s Operating Handbook 2 Section 907 EXTRA 300L XTRA Long Range Wi
91. 39 Economy 2300 183 55 165 452 11 9 165 9 307 136 252 2 81 458 848 Economy 2000 179 45 185 365 9 6 154 5 286 127 235 3 44 526 974 Economy 14000 2700 172 62 186 63 0 16 6 176 6 327 140 259 2 08 350 648 Power 4267 2450 17 0 55 165 46 7 12 3 169 4 314 135 250 2 71 446 826 Economy 2075 17 7 45 135 371 9 8 157 8 292 122 226 3 36 520 963 Economy NOTE Fortemperatures above below Standard ISA increase decrease Range 1 796 and Endurance 1 196 foreach 10 C 18 F above below Standard Day Temperature for particular altitude 2 Leaning with exhaust gas temperature EGT gage For the adjustment Best Power first lean the mixture to achieve the top exhaust temperature peak EGT and then enrich again until the exhaust temperature is 100 F lower than peak EGT For the adjustment Best Economy simply lean the mixture to achieve the top exhaust temperature peak EGT CAUTION Always return the mixture to full rich before increasing power settings Page Date 31 March 2009 5 13 Section 5 Pilot s Operating Handbook Performance XTRA EXTRA 3001 5 11 LANDINGPERFORMANCE Power Idle Runway Concrete Brakes maximum NOTE For every knot 1 852 km h headwind the landing distance can be decreased by 3 On a solid dry
92. 39 Economy 6000 2700 23 6 83 248 77 6 20 5 180 5 334 162 300 1 69 301 557 Power 1829 2500 23 3 75 225 69 8 18 4 174 3 323 158 293 1 88 323 598 Power 2200 232 65 195 50 5 13 3 165 6 307 149 276 2 57 422 782 Economy 2000 22 5 55 165 42 6 11 3 156 1 289 141 261 3 04 472 874 Economy 2000 19 3 45 135 36 5 9 6 145 4 269 131 243 3 58 512 948 Economy 8000 2700 21 8 77 281 78 4 19 4 179 5 882 156 289 1 79 314 582 Power 2438 2675 21 5 75 225 71 9 19 0 177 8 329 155 287 1 82 318 589 Power 2350 21 5 65 195 520 13 7 169 0 313 147 272 2 49 415 769 Economy 2050 214 55 165 43 0 11 4 159 3 295 139 257 2 99 472 874 Economy 2000 18 8 45 185 365 9 6 1484 287 130 241 3 51 517 957 Economy 10000 2700 20 2 72 215 69 6 18 4 178 5 331 151 280 1 88 327 606 Power 3048 2500 19 9 65 195 53 6 142 172 4 319 148 274 2 41 407 754 Economy 2150 19 9 55 165 43 7 11 5 162 5 301 138 256 2 93 469 869 Economy 2000 184 45 135 36 5 9 6 151 4 280 129 239 3 48 522 967 Economy 12000 2700 18 6 67 200 66 2 17 5 177 5 329 146 270 1 96 338 626 Power 3658 2675 184 65 195 55 3 14 9 176 0 326 144 267 2 32 399 7
93. 3thru 921 4 8 October 2009 921 5thru 921 16 19 April 2012 922 1 thru 922 3 5 December 2008 922 4 16 March 2009 922 5 thru 922 8 5 December 2008 923 1 thru 923 8 5 December 2008 924 1 thru 924 1 31 March 2009 924 12 31 October 2013 925 1 thru 925 8 31 March 2009 926 1 thru 926 1 31 March 2009 926 3 19 April 2012 020 4 eei rer rni 31 March 2009 926 5 thru 926 6 19 April 2012 926 7 thru 926 8 31 March 2009 31 October 2013 2 19 April 2012 927 rH 31 October 2013 927 4 thru 927 6 19 April 2012 928 1 thru 928 4 17 January 2013 Page Date 31 October 2013 X TR A Pilot s k e INTRODUCTION This handbook contains 9 sections and includes the material required to be furnished to the pilot by FAR Part 23 It also contains supplementary data supplied by EXTRA Flugzeug produktions und Vertriebs GmbH THIS MANUAL IS FURNISHED TO THE CIVIL AVIATION AUTHORITIES AS A PART OF THE CERTIFICATION MATERIAL FOR THIS MODEL NOTES This Flight Manual applies only to the aircraft whose nationality and registration marks are noted on the title page This Flight Manual is only valid in connection with the la
94. 43 km h higher speeds should be avoided in acrobatics since an unnecessary loss of altitude would occur Torque maneuvers All maneuvers with high angular velocity associated with high propeller RPM must be considered dangerous for the engine crankshaft Although wooden composite propeller blades are used the gyroscopic forces at the prop flange are extremely high Page Date 16 March 2009 4 11 Section 4 Pilot s Operating Handbook Normal Procedures lt XTRA EXTRA 300L CAUTION If performing a gyroscopic maneuver such as flat spin power on or knife edge spin reduce RPM to 2400 in order to minimize the gyroscopic forces 4123 SPIN To enter a spin proceed as follows Reduce speed power idle When the plane stalls Kick rudder to desired spin direction Hold ailerons neutral Stick back positive spinning Stick forward negative spinning The plane will immediately enter a stable spin Ailerons against spin direction will make the spin flatter Ailerons into spin direction will lead to a spiral dive Above apply for positive and negative spinning To stop the spin Apply opposite rudder Make sure power idle Holdailerons neutral Stick to neutral position The plane will recover within 1 2 turn Recovery can still be improved by feeding in in spin ailerons NOTE If ever disorientation should occur during spins normal or inverted one method always wo
95. 6 2 6 2 1 6 3 6 3 1 6 3 2 6 4 6 5 6 6 SECTION6 WEIGHT AND BALANCE AND EQUIPMENT LIST Table of Contents Page GENERAL UI MM IM A T EM 6 3 AIRCRAFT WEIGHING PROCEDURE U u u u u 6 3 Owners Weight and Balance 6 4 CENTER OF GRAVITY CALCULATION SAMPLE PROBLEM 6 5 m EIS 6 7 Weight and Balance Record 6 7 LOADING WEIGHTS AND 2 u u 6 8 WEIGHTS AND MOMENTS 5 11 u u 6 9 EQUIPMENT LIST 6 10 Page Date 20 April 2002 6 1 Section 6 Pilot s Operating Handbook Weight and Balance and Equipment List XTRA EXTRA Left blank intentionally 6 2 Page Date 20 April 2002 Pilot s Operating Handbook Section 6 EXTRA 3001 XTRA Weight and Balance and Equipment List 6 1 GENERAL This section describes the procedure for establishing the basic weight and moment of the aircraft Sample forms are provided for reference Procedures for calculating the weight and movement for various operations are also pro
96. 8 3 BEFORE LANDING 1 Landing approach proceed 2 Airspeed on final maintain 78 KIAS 144 km h 3 Elevator trim adjust NOTE Stall speed will be MTOW 820 55 KIAS 102 km h MTOW 870 kg 57 KIAS 106 km h MTOW 950 kg 60 KIAS 111 km h 4 8 4 NORMAL LANDING 1 Landing perform as practicable with respect to surface and weather condition 2 Touchdown 3 point landing 4 8 Page Date 31 March 2009 Pilot s Operating Handbook Section 4 EXTRA 300L XTRA Normal Procedures NOTE The rudder is effective down to 30 KIAS 56 km h 3 Throttle CLOSE IDLE 4 Braking Minimum required 4 9 GO AROUND Decide early in the approach if it is necessary to go around and then start go around before too low altitude and airspeed are reached Proceed as follows 1 RPM control HIGH RPM Full forward 2 Throttle OPEN Take off power 3 Airspeed Minimum 90 KIAS 167 km h rotate to go around altitude 4 10 SHUTDOWN 1 Boost pump OFF 2 Engine Run for 1 min at 1000 RPM 3 Dead cut check Perform 4 Avionic master switch OFF if installed 5 Mixture IDLE CUT OFF 6 Ignition switch OFF 7 Master switch OFF 4 11 LEAVING THE AIRCRAFT 1 Canopy Close and lock 2 Aircraft Secure 3 Pitot cover Attach 4 Log book Complete Page Date 16 March 2009 4 9 Section 4 Pilot s Operating Handbook Normal Proc
97. 882 Economy 2150 19 3 52 165 43 7 11 5 162 5 301 138 256 3 42 549 1017 Economy 3 Fortemperatures above below Standard ISA increase decrease Range 1 7 and Endurance 1 1 foreach 10 C 18 F above below Standard Day Temperature for particular altitude Best Power or Best Economy see latest issue of Textron Lycoming AEIO 580 B1A Operation and Installation Manual Section Part 3 PN 60 297 32 This RPM setting is not allowed for airplanes equipped with a 3 blade propeller Type MT V 9 B C C 198 25 operated in the normalcategory in which noise protection requirements must be complied with 921 10 Page Date 19 April 2012 Section 921 Lycoming AEIO 580 B1A Engine Pilot s Operating Handbook EXTRA 300L XTRA 921 5 5 Range Configuration 2 00 0065 004 000 006 008 WN 00 006 55914 1 0008 esini2 002 009 005 NN eBue lt 79 9 1 episjno 007 006 002 00 0 gt gt c 9 eunje1eduie apis no Ov 06 00 OL 0 0 02 O Or 921 11 Page Date 19 April 2012 Pilot s Operating Handbook Section 921 EXTRA 300L XTRA Lycoming AEIO 580 B1A Engine 921 5 6 Endurance Configuration 2 00r 09 6 u 008 052 002 4062 eoueinpu3 lt 1 MOd 9 20
98. 9 1 5 Section 1 Pilot s Operating Handbook General XTRA EXTRA 300L 1 7 OIL Cont Average ambient air Mil L6082 Mil 22851 temperature grades ashless dispersant grades 18 C til 21 C SAE 30 SAE 30 40 or 20W40 0 F 70 F 18 C til 32 C SAE 20W50 SAE 20W50 15W50 0 90 F lt 12 10 F SAE 20 SAE 30 or 20W30 single or multi viscosity aviation grade oils see latest issue of Textron Lyc 5 1 No 1014 1 8 LOADING Wing loading 88 8 kg m Normal 76 6 81 3 kg m Acrobatic 1 seat 2 seats Powerloading 3 17 kg hp Normal 2 73 2 90 kg hp Acrobatic 1 seat 2 seats 1 9 TERMINOLOGY Air Speeds CAS Calibrated Air Speed CAS is the same as TAS True Air Speed in standard atmospheric condition at sea level KCAS Calibrated speed in knots GS Ground speed IAS Indicated air speed KIAS Indicated speed in knots TAS True air speed It s the same as CAS compensated for altitude temperature and density Maneuvering speed VNE Never exceed speed VNo Maximum structural crusing speed Vs Stalling speed or minimum steady flight speed Vy Best angle of climb speed Vy Best rate of climb speed 1 6 Page Date 20 April 2002 Pilot s Operating Handbook Section 1 EXTRA 3001 XTRA General Meteorological terminology ISA International standard atmospheric condition OAT Outside airtemperature 1 10 SECONDARY TERMINOLOGY fpm Feet minute ft Feet 0 3048 m in inch 2 2 54 cm m
99. 921 3 921 2 2 Weight Emi ALTRE 921 4 921 2 3 Propeller Lim talons cus 921 4 921 2 4 Operating Placards e 921 4 921 2 5 921 5 921 2 6 921 5 921 2 7 Maximum Operating Altitude 921 5 921 3 EMERGENCY PROCEDURES 921 5 921 4 NORMAL PROCEDURES u 921 5 921 5 PERFORMANGE 921 6 921 5 1 Cruise Performance Chart Configuration 1 921 7 921 5 2 Range Configuration i sessionens iaaa a a a T ii 921 8 921 5 3 Endurance ConfIgUratlon ente rene 921 9 921 5 4 Cruise Performance Chart Configuration 2 921 10 921 5 5 Range Corflgurallon 2 u ces vette endet a tee ate et au Ede 921 11 921 5 6 Endurance Configuration 2 921 12 921 6 WEIGHT AND BALANCE 921 13 921 7 DESCRIPTION e 921 13 Page Date 19 April 2012 921 1 Section 921 mE Pilot s Operating Handbook Lycoming AEIO 580 B1A Engine XTRA EXTRA 300L Left blank intentionally 921 2 Page Date 5 December 2008 Pilot s Operating Handbook Section 921 EXTRA 300L XTRA Lycoming AEIO 580 B1A Engine 921 1 GENERAL As
100. A Electronic Accelerometer 903 ELECTRONIC ACCELEROMETER 903 1 GENERAL The standard equipped accelerometer typ AN 5745 can be replaced by an optional Digital Solid State Accelerometer DSA 12 903 2 LIMITATIONS The instrument markings and placards are provided for the acrobatic category 1 seat only for the acrobatic category 2 seat and for the normal category refer to corresponding limitations Any exceedance of given limitations have to be reported by the pilot and considered by corresponding maintenance or inspection procedure according to the SERVICE MANUAL EA 300 L Instrument markings Electronic Accelerometer DSA 12 red range 12g 10g yellow range gt 10g 80 green range gt 8g yellow range 860 410g red range 410g 120 903 3 EMERGENCY PROCEDURES Not affected 903 4 NORMAL PROCEDURES Not affected 903 5 PERFORMANCE Not affected 903 6 WEIGHT AND BALANCE Not affected 903 7 DESCRIPTION AND OPERATION OF THE SYSTEM The DSA 12 accelerometer measures acceleration in one certain direction The measuring range is between 200 and 20g A clock inside the instrument measures time and date One of the output displays is an LCD with two lines and eight positions per line Positive values of accelerations are always shown in the upper line of the LCD and negative values of acceleration always in the bottom line Page Date 20 April 2002 903 3 Section 903
101. Acro Category 910 6 Page Date 20 April 2002 you YEE YLE 562 977 957 9 EZ i 4 Nay 058 008 05 001 059 009 06 009 059 1 0 004 sgg MNVIONIM YPM OSL gt T 9 310N z 1 O 2 009 048 OMOV 300 028 718 T 058 OMOV 309 MOLN 586 T 006 5600 l OMOV TWWYON 300 056 Sq IH9I3M 5 HOT3M NOIL V 1012 1VO ALLLAVHO dO 910 6 Pilot s Operating Handbook Section 910 EXTRA 300L XTRA Acro 111 Category WEIGHT AND MOMENT LIMITS Weight kg Ibs kg bs Max Cat NORMAL ACRO 950 2095 900 1985 Max T O Cat I 850 1918 1 Max T O 820 1808 Cat ACRO 800 1764 1 750 1653 700 1544 4 650 1432 62 66 70 74 78 82 86 Arm cm 24 4 25 9 27 5 29 1 30 7 32 2 33 8 inch Center of gravity cm inch Aft of the ref datum EXAMPLE At 790 KG 1741 LBS and 640000 kgcm the C G location is 80 0 cm 31 4 aft of ref datum Page Date 20 April 2002 910 7 Section 910 Pilot s Operating Handbook Acro Category XTRA EXTRA 300L 910 7 DESCRIPTIONAND OPERATIONOFAIRCRAFTANDITSSYSTEMS Not affected 910 8 HANDLING SERVICING AND MAINT
102. CE Not affected Page Date 31 March 2009 925 5 Section 925 Pilot s Operating Handbook GARMIN GNC 420W XTRA EXTRA 300L 925 6 925 7 925 7 1 WEIGHT amp CENTER OF GRAVITY Refer to the equipment list in Section 6 of this Handbook SYSTEMDESCRIPTION KEY AND KNOB FUNCTIONS LEFT HAND KEYS AND KNOBS The COM power volume knob controls unit power and communications radio volume Press momentarily to disable automatic squelch control the GPS 420W this control is used only for power The large left knob COM VLOC is used to tune the megahertz MHz value to the left of the decimal point of the standby frequency for the communications transceiver COM orthe VLOC receiver whichever is currently selected by the tuning cursor The small left knob COM VLOC is used to tune the kilohertz KHz value to the right of the decimal point of the standby frequency for the communications transceiver COM or the receiver whichever is currently selected by the tuning cursor Press this knob momentarily to toggle the tuning cursor between the COM and VLOC frequency fields The COM flip flop key is used to swap the active and standby COM frequencies Press and hold to select emergency channel 121 500 MHz RIGHT HAND KEYS AND KNOBS The range key RNG allows you to select the desired map scale Use the up arrow side of the key to zoom out to a larger area or the down arrow side to zoom in to a s
103. D1000 PILOT PFD may be forced to shut down by first pulling the PFD circuit breaker and then pressing and holding the REV button for at least 5 seconds 924 7 4 DISPLAY SCREENAND CONTROLLAYOUT 1 Reversion Control 2 Range Control 3 Menu Control 4 TPS Tapes ON OFF Control 5 Minimum indication ON OFF Control 360 ARC HSI View Control 7 ON OFF logic Control 6 Not Used 9 Right Control Knob 10 Left Control Knob 11 Not Used 12 Not Used 13 Not Used 14 Micro SD Card slot 15 Automatic Dimming Photocell 16 Attitude Indicator 17 Aircraft Symbol 19 Roll Pointer 20 Slip Skid Indicator 21 Airspeed Indicator Tape 22 Selected Airspeed Field 23 Airspeed Drum Pointer 24 Altitude Alert 25 Selected Altitude Field 26 Altitude Drum Pointer 27 Altitude Tape 34 True Airspeed 35 Barometric Pressure Setting Field 36 Ground Speed 37 OAT 36 Wind Direction Arrow 39 Wind Direction and Speed 36 39 Data Bar 40 Selected Source Information Field 42 Selected Heading Field 43 Vertical Speed Digital Value 44 Vertical Speed Tape 45 Left Control Knob state 46 Right Control Knob state 52 Magnetic Heading 53 Compass Scale 54 Hot Key legend 58 Heading Bug 59 Airspeed Bug 60 Altitude Bug Figure I Display Features 924 6 Page Date 31 March 2009 Pilot s Operating Handbook Section 924 EXTRA 300L XTRA ASPEN EFD1000 PILOT P
104. D1000 PILOT PFD system is a flat panel LCD flight instrument that presents the pilot with displays of attitude airspeed altitude vertical soeed slaved compass slip skid and rate of turn information The display head incorporates a solid state Air Data and Attitude Heading Reference System ADAHRS to provide data for the flight instruments The ADAHRS system uses data from its internal solid state rate gyros and accelerometers pitot and static sensors solid state magnetometer and solid state temperature probes all contained withinthe display head and RSM to derive the aircraft attitude and air data solutions NOTE Although intuitive a reasonable degree of familiarity is required to use the EFD1000 PILOT PFD 924 4 Page Date 31 March 2009 Pilot s Operating Handbook 2 Section 924 EXTRA 300L XTRA ASPEN EFD1000 PILOT PFD 924 7 2 PILOT CONTROLS OVERVIEW Pilot interaction with the EFD1000 PILOT PFD is accomplished through two knobs with push rotate function and 11 buttons located onthe display bezel Refer to Figure 2 Two control knobs are used to control pilot settable bugs and references Three lower push buttons located between the control knobs are not usedin the EFD1000 PILOT PFD model Three dedicated buttons onthe upper side of the right bezel control map range display reversion and provide access to the main menu Up to five soft keys on the lower half of the right bezel control frequently used commands These f
105. DER THE AGENCIA NACIONAL DE AVIACAO CIVIL REQUIREMENTS Table of Contents Paragraph Page 927 1 GENERAL 927 3 927 2 IMITATIONS i 927 4 927 2 1 ENGINE r M 927 4 927 2 2 KINDS OF OPERATIONAL LIMITS vices sanct tite atico cort cna do pe nac ca 927 4 927 2 3 5 0 8 927 4 927 3 EMERGENCY PROCEDURES 927 4 927 4 NORMAL PROCEDURES III va xao nope 927 4 927 5 PERFORMANCE M 927 4 927 6 WEIGHT amp CENTER OF GRAVITY U eene messen 927 5 927 7 SYSTEM DESCRIPTION soc cn soon accru 927 5 927 8 HANDLING SERVICING AND MAINTENANCE mennan nne 927 5 EASA Approved On Behalf of ANAC of Brazil Maximilian Maas European Aviation Safety Agency Page Date 31 October 2013 927 1 Section 927 mE Pilot s Operating Handbook AIRPLANES REGISTERED IN BRAZIL XTRA EXTRA 300L Left blank intentionally 927 2 Page Date 19 April 2012 Pilot s Operating Handbook 2 Section 927 EXTRA 300L XTRA AIRPLANES REGIS
106. Duci Ya n mmn c Yr nain Dn aen 907 3 907 5 A POE 907 4 907 6 WEIGHT AND BALANCE aca aaa nane d dcr ava 907 5 907 7 DESCRIPTION OF THE SYSTEM _ UI naaa 907 6 907 8 HANDLING SERVICING AND MAINTENANGCE 907 6 Page Date 16 March 2009 907 1 Section 907 junii Pilot s Operating Handbook Long Range Wing Tank Capacity XTRA EXTRA 300L Left blank intentionally 907 2 Page Date 20 April 2002 Pilot s Operating Handbook Section 907 EXTRA 300L Long Range Wing Tank Capacity 907 907 1 907 2 907 3 907 4 LONGRANGE WING TANK CAPACITY GENERAL The leading edge wing tank on the EA 300 L equipped with the long range tank capacity features two tank compartments on either wing side The compartments are separated by a slosh rib LIMITATIONS FUEL Minimum grade aviation gasoline 100 100LL for alternate fuelgrades see latest revision of Lyc 5 1 No 1070 Total fuel capacity 205L 54 1 US Gallons Wingtank 154 L 2 x 77 L 40 7 US Gallons Acro amp Center Tank 51L 13 4 US Gallons Usable fuel capacity in the system 199 5 L 52 7 US Gallons For acrobatic flight wing tanks must be empty Usable fuel capacity for acrobatic 45 5 L 12 0 US Gallons WEIGHT LIMITS M
107. E Not applicable 914 6 Page Date 15 December 2005 Pilot s Operating Handbook TR A EXTRA 300L Paragraph 915 1 915 1 1 915 1 2 915 1 3 915 1 4 915 1 5 915 1 6 9151 7 915 2 915 3 915 3 1 915 4 915 5 SECTION 915 GARMIN GTX 330 TRANSPONDER Table of Contents Page ET 915 3 Mod Selection Keys IEEE 915 4 Code SCE CON 915 4 Keys for other GTX 330 915 5 FHUMICTIONDISIAY 915 5 Configuration EPI 915 6 Altitude trend 915 6 Failure ANMUMCIATION 915 6 uu 915 7 EMERGENCY PROCEDURES 915 7 Important 61626 915 7 NORMAL PROCEDURES I n 915 7 PERFORMANCE 915 7 Page Date 15 December 2005 915 1 Section 915 mE Pilot s Operating Handbook GARMIN GTX 330 Transponder XTRA EXTRA 300L Left blank intentionally 915 2 Page Date 15 December 2005 Pilot s Operating Handbook Section 915 EXTRA 300L GARMIN GTX 330 Transponder 915 1 GENERAL The Garmin GTX330 panel mounted Mode S Transponderis aradio transmitter and receiverthat fulfills the role of the airborne beac
108. ED UU pde top Edd 4 p Page Date 17 January 2013 Pilot s Operating Handbook Section 9 EXTRA 300L XTRA Supplements 9 SUPPLEMENTS 9 1 Introduction Section 9 Supplements of the Pilot s Operating Handbook contains all information neces sary for a safe and efficient operation of the airplane when equipped with one or more of the various optional systems and equipment not provided with the standard airplane 9 2 Notes The described systems and equipment are certified by the EASA for the EXTRA 300 L Pages and contents of this section must not be exchanged and alterations of or additions to the approved contents must not be made without the EXTRA Flugzeugproduktions und Vertriebs GmbH EASA approval The editor has the copyright of these Supplements and is responsible for edition of revisions The log of effective pages is found on the preceding pages of this Pilot s Operating Handbook Each Supplement section e g steerable tailwheel covers only a single system device or piece of equipment 15 a self contained miniature Pilot s Operating Handbook The owner is responsible for incorporating prescribed amendments and should make notes about these on the records of amendments It is responsibility of the pilot to be familiar with the contents of relevant supplements POH Supplements must be in the airplane for flight operations when the subject equipment is installed or special operations are to be perfor
109. ELT is activated it is transmitting a 121 5 MHz distress signal Therefore all activations of the ELT should be kept to a minimum Local or national regulations may limit testing of the ELT or impose special requirements or conditions to perform testing For the self test Artex recommends that the ELT for no more than 5 seconds Testing should occur during the first 5 minutes after the hour Page Date 19 April 2012 926 5 Section 926 Pilot s Operating Handbook ARTEX 406 ELT XTRA EXTRA 926 8 HANDLING SERVICING AND MAINTENANCE 926 8 1 TRANSMITTERTEST ARTEX recommends that the ELT be tested every 1 2 months Follow the steps outlined in the 926 8 2 SELF TEST paragraph NOTE The self test time is accumulated in a register on the battery pack The register records activation time in 30 second increments so all activations will countas atleast 30 seconds even if the actual time is much less Total allowable time is 60 minutes as determined by FAR 91 207 and RTCA DO 204 After this time has been accumulated a 7 flash error will be presented after the self test The battery must be replaced at this point for the ELT to remain in compliance Always follow ELT testing requirements per local or national authorities Always perform the tests within the first 5 minutes of the hour Notify any nearby control tower of yourintentions in accordance with AC 43 13 If outside ofthe US alwaysfoll
110. ENANCE Not affected 910 8 Page Date 20 April 2002 t 911 SINGLE SEAT Table of Contents Paragraph Page 911 1 GENERA erni Pr 911 3 911 2 n 911 3 911 3 EMERGENCY PROCEDURES ssasasasasasassksa 911 3 911 4 NORMAL PROCEDURES 911 3 911 5 PERFORMANCE Au 2 a aus au aaa 911 3 911 6 WEIGHT AND BALANCE AND EQUIPMENT 911 3 911 7 DESCRIPTION OF THE SYSTEM ntn ne cna nit aan raum m 911 3 911 8 HANDLING SERVICE AND MAINTENANCE 3 Page Date 20 April 2002 911 1 Section 911 Pilot s Operating Handbook Single Seat Canopy XTRA EXTRA 300L Left blank intentionally 911 2 Page Date 20 April 2002 Pilot s Operating Handbook Section 911 EXTRA 300L XTRA Single Seat Canopy 911 911 1 911 2 911 3 911 4 911 5 911 6 911 7 911 8 SINGLE SEAT CANOPY GENERAL For airshow performances the standard canopy can be replaced by a single seat canopy which gives a gorgeous appearance LIMITATIONS With the single seat canopy installed the aircraft is limited to the categories NORMAL and ACRO In the NORMAL category the aircra
111. ERGENCY PROCEDURES Not affected 906 4 NORMALPROCEDURES The Normal Procedures have to be changed in Chapter 4 5 Take Off Procedure section 4 5 1 Before take off f the P 1000 RPM indicator is installed the mag drop test has to be carried out in the following manner Magneto check Engine RPM 1800 min Pay attation to the three small LEDs in the Status area on the upper left corner of the P 1000 face Ignition switch position LEFT Status area Right red LED illuminates Display shows RPM drop Page Date 19 April 2012 906 3 Section 906 Pilot s Operating Handbook Digital RPM Indicator XTRA EXTRA 300L Ignition switch position RIGHT Status area Left red LED illuminates Display shows RPM drop Ignition switch position BOTH Status area Right and left red LED OFF The middle LED should be OFF otherwise the difference is more than permissible NOTE During the short circuit grounding of a single magneto the respective red LED has to be illuminated The maximal allowed RPM drop at 1800 RPM is 175 The maximal RPM difference between the magnetos should not exceed 50 min identified by the illuminated yellow LED 906 5 PERFORMANCE Notaffected 906 6 WEIGHT AND BALANCE Not affected 906 7 DESCRIPTION AND OPERATION OF THE SYSTEM The operation of the indicator is straight forward After power is supplied to the indicator the engine is started and the self tests are p
112. ERING Hot Key 5 enables disables the GPS Steering 924 7 9 BACKLIGHT CONTROL The EFD1000 PILOT PFD includes an adjustable LCD backlight that provides both automatic and manual brightness adjustments over a wide dimmable range A single bezel mounted photocell measures the ambient light allowing an automatic dimming mode to be selected by the pilot Manual dimming control is enabled by the pilot to override the photocell input and adjust the display to any desired intensity level except off In either mode the bezel key backlighting is maintained at a fixed brightness level To adjust backlight intensity press the MENU button and then press the left control knob to toggle between auto BRT AUTO and manual brightness BRT ADJUST control To manually adjust the brightness with BRT ADJUST displayed above the left knob rotate the knob until the desired brightness level is set Valid brightness settings are 1 to 100 On power up the display defaults to AUTO brightness control When operating onthe internal battery backlight intensity setting is capped ata value of 70 for both manual and automatic operation Under extreme temperature conditions such as may be encountered during ground operations on extremely hot days the system backlight will automatically dim to an intensity of 30 whenever internal sensors determine that the system operating temperature has exceeded 70 C Should this occur the pilot should take steps to reduce the
113. FD 924 7 5 CONTROL KNOBS General Two control knobs on the EFD bezel are used to adjust pilot editable data fields The left knob adjusts data fields on the left side of the display and the right knob adjusts data fields on the right side of the display The knob logic includes active and inactive states to prevent inadvertent adjustment of editable fields After 10 seconds of inactivity the knob returns to an inactive state and also returns to the home state defined for that knob A single push activates an inactive knob Pushing the knob again will advance the knob to the next editable field if applicable in a round robin sequence When inactive the knob legend is rendered in cyan Once activated the knob legend and associated data field and bug where appropriate are rendered in magenta Left control knob The left control knob adjusts the Indicated Airspeed Bug editable fields andthe Course CRS refer to Aspen Pilot s Guide for more information The home state for the left knob is CRS Right control knob The right control knob controls Heading Bug Altitude Bug and Barometric Pressure Setting editable fields in that order The home state for the right knob is HDG 924 7 6 SETTING FLIGHT INSTRUMENTS Thefollowing procedures are used to adjust pilot editable data on the EFD1000 PILOT PFD Heading Bug Set To setthe heading bug repeatedly PUSH the righ
114. Handbook 9 SUPPLEMENTS Doc No 06701 1 Table of Contents Section Pages 9 Supplements cde teed dead doce a eiu eee 4 p 901 Steerable Tail 4 p 902 Electric Pedal Adjustment u u u u u 4p 903 Electronic 10 p 94 Emergency Locator Transmitter u 8 p 905 External 6 p 906 Digital RPM Indicator 6 p 907 Long Range Wing Tank 6 p 908 121 Airtow HOOK 8 p 909 Smoke rincon erect eres ine rapere p cx age veo CE eure 6 p 910 ACRO UN Category 8 p 911 Single Seat Canopy uuu 4 p 912 FILSER TRT 600 8 p 913 FILSER TRT 800 Transpondetr l J 8 p 914 GARMINGTX327 6 p 915 GARMINGTX33
115. ILL ON NOTE The refilling should start within max 30 sec If this is not the case the refill lines fittings and filter if installed have to be checked for soiling or leaks Refilling procedure can be supported by reducing the suction height e g lifting the canister The fully filled status is sensed by the floating device which automatically switches the refilling off After automatic refill shut off 3 Switch SMOKE REFILL OFF 4 Refill hose DISCONNECT 909 4 Page Date 16 March 2009 Pilot s Operating Handbook Section 909 EXTRA 300L X TRA Smoke System CAUTION A shut off failure of the refill process can be recognized by smoke oil spilling out of the vent line In this case turn off refill switch The floating device switch in the main smoke oil tank has to be checked accordingly B SMOKE GENERATION 1 Bad weather window and ventilation CLOSE 2 SMOKE ARM Switch ON 3 Manifold Pressure minimum 20 Hg 4 Switch in the throttle lever forsmoke generation ON OFF NOTE It is recommended to operate the smoke system only in forward flight because during reverse maneuvers for example tail slide smoke might enter the cockpit via the air vents 909 5 PERFORMANCE Not affected 909 6 WEIGHT AND BALANCE s s e Specific Weight of the paraffin oil 0 85 kg Litre NOTE The smoke system does notfeature a capacity dipstick Int
116. IRCRAFT Theaircraft EXTRA 300L is designed and developed by EXTRA Flugzeugproduktions und Vertriebs GmbH Flugplatz Dinslaken 46569 H nxe Federal Republic of Germany in accordance with the U S Federal Aviation Regulations part 23 categories normal and acrobatic to fullfill the primary flight training normal operation rules and acrobatic training up to the unlimited acrobatic level EXTRA 300 L is a light weight robust single piston engined two seat aircraft with a fuselage structure in tig welded steel tube construction The landing gear wing and tail are made of epoxy reinforced with glass and carbonfiber The items are qualified up to 72 C 161 6 F Not to exceed this temperature limit an appropriate colour specification for composite structure is given by the manufacturer document EA 03205 19 To check the temperature inside the cockpit potential green house effect a reversible temperature indicator STRUCTURAL OVERHEAT INDICATOR is applied on the upper side of the wing main spar in the carry through section After reaching the temperature limit of 72 C 161 6 F the word RISK appears on the red spot of this structural overheat indicator immediately and flying is prohibited When the structure cools down below this temperature limit the word RISK disappears and you may go on with the preflight checklist Below 72 C 161 6 b At 72 C 161 6 F or above STRUCTURAL i eae STRUCTURAL
117. ISE 4 7 4 8 LANDING PROCEDURES Ul UU U U UU 4 8 4 8 1 Descent usukuq aT basada 4 8 4 8 2 4 8 4 8 3 I UE 4 8 4 8 4 PE 4 8 4 9 GO AROUND m 4 9 4 10 SHUTDOWN Lx uu PARE 4 9 4 11 AFTER LEAVING THE AIRCRAFT U u u u u u 4 9 4 12 ACROBATIC MANEUVERS 4 10 4 12 1 Eee E EE E E E E E E 4 10 4 12 2 niy 4 10 4 12 3 a 4 12 Page Date 31 March 2009 4 1 Section 4 Pilot s Operating Handbook Normal Procedures EXTRA 300L Left blank intentionally 4 2 Page Date 20 April 2002 Pilot s Operating Handbook Section 4 EXTRA 300L XTRA Normal Procedures SECTION 4 NORMAL PROCEDURES 4 0 GENERAL 4 0 1 AIRSPEEDS FOR NORMAL OPERATION CATEGORY ACRO NORMAL 1 seat 2 seats KIAS km h KIAS km h KIAS km h Start Rotating Speed 60 111 62 115 65 120 Climb Vx 87 161 89 165 93 172 96 178 99 183 104 193 Recommended No
118. Instruments UI5934PD 3 A 134 0 39 0 66 1 Altimeter front metric Winter 4110 0 33 0 66 1 Altimeter front metric United Instruments UI5934PD 3M 665 0 39 0 66 A 1 Altimeter front ft Mikrotechna Praha LUN 1128 10B6 0 59 0 65 A 1 Altimeter rear United Instruments UI5934PD 3 A 134 0 39 1 62 R 1 Altimeter rear metric Winter 4110 0 33 1 62 A 1 Altimeter rear metric United Instruments UI5934PD 3M 665 0 60 1 62 A 1 Altimeter rear ft Mikrotechna Praha LUN 1128 10B6 0 59 1 61 A 1 Radar Altimeter Anten FreeFlight TRA 3000 0 68 2 33 1 incl Digital Indicator TRI20 0 34 1 55 1 Altitude Encoder ACK A 30 0 15 1 50 1 Airspeed Ind front Winter 6533 321 0 21 0 65 1 Airsp Ind front metrig Winter 6531 321 0 21 0 65 O 6 12 Page Date 31 October 2013 Pilot s Operating Handbook XTRA Section 6 EXTRA 300L Weight and Balance and Equipment List QTY ITEM MANUFACT PART OR P N WEIGHT ARM MARKIF REQUIRED R m INSTALLED OPTIONAL O ALTERNAT A 1 Airspeed Ind front United Instruments UI8030 B 835 0 32 0 65 1 Airspeed Ind front United Instruments UI8030 B 898 0 32 0 65 A dual scale 1 Airspeed Ind front Mikrotechna Praha LUN 1106 K2B4 SC 0 50 0 65 A kts 1 Airspeed Ind front Mikrotechna Praha LUN 1106 P2B4 SC 0 50 0 65 A km h 1 Airspeed Ind rear Winter 6533 321 0 21 1 61 R 1 Airsp Ind rear metric Winter 6531 321 0 21 1 61 A 1 Airspeed Ind re
119. LIGHT 69 30 Page Date 16 March 2009 2 7 Section 2 Pilot s Operating Handbook Limitations XTRA EXTRA 300L 2 9 2 ACROBATIC FLIGHT 10g 10g for 1 seat occupied MTOW 820 kg 1808 Ibs 8g 89 for 2 seat occupied MTOW 870 kg 1918 Ibs 2 10 FLIGHT CREW LIMITS Minimum crew is one pilot in the rear seat 2 persons in both categories Normal and Acrobatic Pilot in command seat is the rear seat Co pilot or passenger seat is the front seat Noise optimized headsets are required 2 11 KINDS OF OPERATIONAL LIMITS Only VFR flights at day are allowed The A C may be operated at OAT from 20 C 4 F to 44 C 111 F Below temperatures of 10 C 14 F the oil vent line must be modified by the low temperature kit breather line Flight in known icing conditions is prohibited Smoking is prohibited 2 114 STRUCTURAL TEMPERATURE COLOUR LIMITATION Structure is qualified up to 72 C 161 6 F Structure temperatures composite above 72 C 161 6 F not permitted Not to exceed this temperature limit color specification for composite structure manufacturer document EA 03205 19 has to be complied with To check the temperature inside the cockpit potential green house effect a reversible temperature indicator STRUCTURAL OVERHEAT INDICATOR is applied on the upper side of the wing main spar in the carry through section After reaching the temperature limit of 72 C
120. NCE 8 1 INTRODUCTION a The airplane owner should establish contact with the dealer or certified service station for service and information b All correspondence regarding the airplane must include its serial number which is stamped on a plate on the L H rear part of the fuselage c A service manual with revision service may be procured from the manufacturer 8 2 AIRPLANE INSPECTION PERIODS As required by national operating rules all airplanes must pass a complete annual inspection every twelve calendar months In addition to the annual inspection airplanes must pass a complete inspection after every 100 flights hours with a minor check after 50 hours The Airworthiness Authority may require other inspections by the issuance of airworthiness directives applicable to the aircraft engine propeller and components The owner is responsible for compliance with all applicable airworthiness directives and periodical inspections 8 3 PILOT CONDUCTED PREVENTIVE MAINTENANCE Pilots operating the airplane should refer to the regulations of the country of certification for information of preventive maintenance that may be performed by pilots All other maintenance required on the airplane is to be accomplished by appropriately licensed personnel Airplane dealer should be contacted for further information Preventive maintenance should be accomplished with the appropriate service manual 8 4 ALTERATIONS OR REPAIR Alterations or repairs of
121. NG TANK 0 the separate 1201 hatch upper cowling ERES GAL FUEL 8 CENTER gt 45 5 L USABLE SELECTOR 12 0 US GAL in both cockpits near selector valve handle NOSE DOWN lt NEUTRAL gt NOSE UP near the handle at the right side TRIM in the rear cockpit WING TANK on the rear instrument panel under MUST BE EMPTY FOR ACROBATICS 2 fuel capacity indicator amp CENTER TANK SHOWS ZERO IN LEVEL FLIGHT BELOW 11 L 2 9 US GAL UNUSABLE FUEL 5 5 L 1 5 US GAL Page Date 16 March 2009 2 9 Section 2 Pilot s Operating Handbook Limitations XTRA EXTRA 300L THE REMAINING FUEL IN LEVEL FLIGHT ___ on the rear instrument panel CANNOT BEUSED SAFELY under the acro amp center tank fuel WHENINDICATOR READS ZERO capacity indicator ACROBATIC x 10G 1 PILOT 89 2 PERSON ON BOARD MTOW 820 KG 1808185 870 1918 LBS N NORMAL 6 G 3 950 KG 2095 LBS ACROBATICS INCL SPIN NOT APPROVED in both cockpits PNUD NS pump switch on the instrument panel in the rear cockpit ON OFF both cockpits USE OF HEADSET IS REQUIRED on the right side of both USE OF PARACHUTE IS RECOMMENDED instrument panels NO BAGGAGE on Lexan cover aft pilot s seat if installed MAGNETIC near Mag Dir Indicator DIRECTION INDICATOR CALIBRATION
122. NT The IDENT push button causes the special position identification pulse SPI to be transmitted for a period of 18 seconds FID In the Standby Mode the Aircraft Identification Flight Identification and Aircraft Address can be checked by pressing the push button FID The Flight Identification is displayed on the right side of the lower line By pressing the button FID for more than 3 seconds the input mode can be set or the Flight Identification can be changed FLAGS SQUITTER FLAG When the extended squitter is active the letter S is displayed on the left top side of the display As the squitter is a periodic signal the displayed S is blinking REPLY FLAG In case of the transponder replying to interrogations the letter R is displayed on the left top side of the display 913 4 Page Date 15 December 2005 Pilot s Operating Handbook Section 913 EXTRA 300L XTRA FILSER TRT 800 Transponder IN FLIGHT FLAG When there is an undercarriage switch installed the display can toggle between the letters F whether the aircraft is in flight condition or the letter whether the aircraft is in condition The flag is displayed on the right bottom side of the display BATTERY FLAG If the power supply to the transponder drops below 10 Volts the flag BAT appears and starts flashing 913 1 2 SYSTEM OPERATION The transponder should be turned off before starting and shutting down aircraft engi
123. ODES 7600 Loss of communications 7500 Hijacking 7700 Emergency All secondary surveillance radar sites are ready to receive this code at all times See the Airman s Information Manual AIM for a detailed explanation of identification codes 923 4 NORMALPROCEDURES Notapplicable 923 5 PERFORMANCE Notapplicable Page Date 5 December 2008 923 7 Section 923 mE Pilot s Operating Handbook GARMIN GTX 328 Transponder XTRA EXTRA 300L Left blank intentionally 923 8 Page Date 5 December 2008 ir aps SECTION 924 ASPEN EFD1000 PILOT PFD Table of Contents Paragraph Page 924 1 GENERAL ELLE RECEN 924 3 924 2 LIMITATIONS qu u 924 3 924 2 1 Placards and Decals secs sav suse te sat bd ou a Edda dd 924 3 924 3 EMERGENCY PROCEDURES 2 sss 924 4 924 4 NORMAL PROCEDURES U u u u au 924 4 924 5 ua 924 4 924 6 WEIGHT amp CENTER OF GRAVITY ten nene omnei ane nue 924 4 924 7 SYSTEM DESCRIPTION eco 924 4 924 7 1 Qenera uu M 924 4 924 7 2 Pilot Controls OVerVIeW ee 924 5 924 7 3 Power Control m 924 5 924 7 4 Display Screen and Control Layout u unu anun a kunam a 924 6 924 7 5 Control KrioDS ge eed ae
124. Paragraph Page 923 1 icd nime auqa 923 3 923 1 1 Mode SelectioniKeys sehen Aedui ae a 923 4 923 1 2 Code SelectlOrn uisu E ea Ra 923 4 923 1 3 Keys for other G TX 328 FUNCIONS e rit te tna 923 5 923 1 4 F ncion Display eT Pe 923 5 923 1 5 Contiguiration ModE uu u D W 923 6 923 1 6 Altitude trend indicator 923 6 923 1 7 Failure E 923 6 923 2 Bale rmt 923 7 923 3 EMERGENCY PROCEDURES 923 7 923 3 1 Important CodeS 923 7 923 4 NORMAL PROCEDURES u O 923 7 923 5 PERFORMANCE ua 923 7 Page Date 5 December 2008 923 1 Section 923 mE Pilot s Operating Handbook GARMIN GTX 328 Transponder XTRA EXTRA 300L Left blank intentionally 923 2 Page Date 5 December 2008 Pilot s Operating Handbook 2 Section 923 XTRA GARMIN GTX 328 Transponder GENERAL The Garmin GTX 328 panel mounted Mode S VFR Transponderis a radio transmitter and receiver that fulfills the role ofthe airborne beacon equipment according to the requirements of the Air Traffic Radar Beacon System ATCRBS Its functionality includes replying to ATCRBS Mode A and C and Mode S interrogations The Mode S function will allow the ground station to individually select the aircraft by its Aircraft Add
125. RMAL PROCEDURES Notaffected 927 5 PERFORMANCE Notaffected 927 4 Page Date 19 April 2012 Pilot s Operating Handbook Section 927 EXTRA 300L XTRA AIRPLANES REGISTERED IN BRAZIL 927 6 WEIGHT amp CENTER OF GRAVITY Not affected 927 7 SYSTEMDESCRIPTION Not affected 927 8 HANDLING SERVICING AND MAINTENANCE Not affected Page Date 19 April 2012 927 5 Section 927 mE Pilot s Operating Handbook AIRPLANES REGISTERED IN BRAZIL XTRA EXTRA 300L Left blank intentionally 927 6 Page Date 19 April 2012 555 2119 Handbook SECTION 928 LANDING LIGHT Table of Contents Paragraph Page 928 1 GENERAL A 928 3 928 2 LIMITATION ull Hs 928 3 928 3 EMERGENCY PROCEDURES 1 5 5 dni aiaa a Ya 928 3 928 4 NORMAL PROCEDURES 928 3 928 5 dde i ez PED 928 3 928 6 WEIGHT AND BALANGE J I tcc ne eren net ccena ice 928 3 928 7 DESCRIPTION OF THE SYSTEM nennen nnn tnmen nnns sinn nnne 928 3 928 8 HANDLING SERVICING AND MAINTENANGCE 928 4 Page Date 17 January 2013 928 1 Section 928 Pilot s Operating Handbook Landing Light XTRA EXTRA 300L 300 Left blank intentional
126. RST SECONDS AFTER THE POWER ON All LEDs are lighted up during the first two seconds after the power on of the instrument Both the Current Extreme Value and the Total Extreme Value are reset to 0g The LCD shows A 0 0g 0 09 After two seconds the Instrument changes automatically into the Normal Operating Mode 2 THE NORMAL OPERATING MODE In the Normal Operating Mode the instrument outputs the Instantaneous Acceleration and the Current Extreme Values The Instantaneous Acceleration is shown as a bar on the LED Display Furthermore one LED indicates the positive and another one indicates the negative Current Extreme Value The Current Extreme Values are also shown on the LC Display and signed with an A for example 7 39 A 3 59 903 6 Page Date 20 April 2002 Pilot s Operating Handbook 2 Section 903 EXTRA 300L X TRA Electronic Accelerometer 3 RESET OF THE CURRENT EXTREME VALUES Push button once S1 If you want to reset the Current Extreme Value to Og for example you want to measure the extreme values of the next flight figure you have to push S1 once In this case all LEDs are lighting up for two seconds the LC Display is showing A 0 09 004 and the Current Extreme Value is reset to 00 On condition you push S1 for another time during this two seconds you get to other submenues else the instrument returns into the Normal Operating Mode All LEDs
127. RT10427 1 Magneto L H Slick 6393 2 30 0 15 A 1 Magneto R H Slick 6350 2 00 0 15 A 1 Slick Start Unison 551001 0 27 0 02 A 4 Shock Mounts Lord J 7764 20 1 70 0 29 R 4 Shock Mounts Barry Controls 94016 02 1 70 0 29 A 1 Exhaust System EXTRA 63104A0 7 65 0 40 R 6in2 Sky Dynamics 2 Exhaust Gomolzig EA300 NSD 9 60 0 80 Silencer GO3 606500 1 Exhaust System Gomolzig EA300 606000 8 20 0 39 A 6 in 1 with Silencer 1 Fuel Injector Bendix RSA 10 AD 1 3 90 0 68 R 1 El Fuel Pump Weldon Tool 8120 M or B8120 M 1 10 0 04 R 1 Oil Cooler Stewart Warner 8406 R 1 40 0 90 R 1 2 Oil Cooler Stewart Warner 8406 R 1 40 0 20 1 Low Temperature Extra 83301 0 20 0 01 A Breather Line Kit 1 Single Oilcooler rear Niagara NDM 20009A 1 81 0 22 A 1 Single Oilcooler rear Aero Classics 8000353 1 65 0 22 A 1 Set Fuel Oil amp Sens div MS28741 with 6 30 0 21 R Hoses in Eng Comp firesleeve 1 Set Fuel Oil amp Sens Parker Stratoflex PTFE Type 124J 4 90 0 21 A Hoses in Eng Comp or Aeroquip or AE466 dual Oil Cooler Sys 1 Set Fuel Oil amp Sens Parker Stratoflex PTFE Type 124J 3 70 0 15 A Hoses in Eng Comp or Aeroquip or AE466 single Oil Cooler Sys 1 Set Fuel Hoses div MS28741 2 10 0 45 R in Cabin Comp 1 Set Fuel Hoses Parker Stratoflex PTFE Type 124 1 40 0 45 A in Cabin Comp or Aeroquip or 666 1 Set Sens Hoses Knapp Hoerbiger HS3MA OR H3MM 0 15 0 82 R Oil Fuel amp MA Press 1 RPM Vernier Control AC
128. S Products A 750 30 1200 0 71 0 82 1 Mixture Vernier Control ACS Products A 750 20 1080 0 65 0 94 R 1 Throttle Control Teleflex F303 03250 0 56 0 60 R or CC330 10 1 Propeller MT Propeller MTV 9 B C C200 15 30 40 1 15 R 1 Spinner MT Propeller P 208 B 0 8 1 20 R 1 Spinner MT Propeller P 810 2 0 8 1 20 A 6 10 Page Date 31 October 2013 Pilot s Operating Handbook XTRA Section 6 EXTRA 300L Weight and Balance and Equipment List QTY ITEM MANUFACT PART OR P N WEIGHT ARM REQUIRED kg m INSTALLED OPTIONAL O ALTERNAT A 1 Propeller MT Propeller MTV 14 B C C190 17 29 80 1 15 1 Spinner MT Propeller P 238 A 0 8 1 20 1 Spinner MT Propeller P 967 0 8 1 20 A 1 Propeller MT Propeller MTV 9 B C C 198 25 30 50 1 15 1 Spinner MT Propeller P 810 2 0 8 1 20 1 Cowling GRP EXTRA 23205 01 amp 02 9 80 0 52 R EXTRA 83802 1 1 Cowling CRP EXTRA 23205 301 amp 302 8 80 0 52 A EXTRA 83802 1 1 Cowling CRP EXTRA 83001 0 9 20 0 57 1 Cowling GRP EXTRA 83003 0 10 60 0 57 1 Cowling CRP EXTRA 8E001 0 9 20 0 57 A incl Landing Light provision 1 Governor Woodward A 210 988 1 10 0 91 R 1 Governor MT Propeller P 880 5 1 10 0 91 A 1 Governor MT Propeller P 880 41 1 10 0 91 A 7 Switches Cutler Hammer div 0 28 1 63 R 7 Switches Kissling div 0 28 1 63 A 11 Circuit Breaker Potter amp Brumfield div 0 50 1 60 R 11 Circuit Breaker ETA or Klixon
129. T ENGINES Because of the fact that the fuel percolates and the system must be cleared of vapor it is recommended to use the same procedure as outlined for cold engine start 4 4 TAXIING THE AIRCRAFT 1 Canopy CLOSE AND LOCK 2 Brake CHECK 3 Altimeter Set on QFE or QNH Scale error max 60 ft 4 Avionic master switch ON 5 Electrical equipment ON 6 Radio Set and test 7 Mixture Leave in FULL RICH position Operate only with the propeller in minimum blade angle High RPM Warm up at approximately 1000 1200 RPM The engine is ready for take off when the throttle can be opened without the engine faltering 4 6 Page Date 20 April 2002 Pilot s Operating Handbook Section 4 EXTRA 300L XTRA Normal Procedures 4 5 TAKE OFF PROCEDURE 4 5 1 BEFORE TAKE OFF Before you line up at the runway for take off Check oil pressure and oil temperature Check the magnetos at 1800 RPM Allowed drop is 175 RPM max difference 50 RPM Check Alternator Output Move also the propeller control through its complete range to check operation and return to full HIGH RPM position Turn boost pump ON check indicator movement on the fuel flow gauge NOTE The RPM Gauge is electronically operated To check the magnetos the RPM source switch must be set to the same magento as the igintion switch Otherwise the gauge will show zero 4 5 2 TAKE OFF Set throttle smoothly to max and let the airspeed go up
130. TEM On instrument panel above circuit breaker row __ On instrument panel BREAKER below circuit breaker row 909 3 EMERGENCY PROCEDURES FAILURE OF THE SMOKE SYSTEM 1 Switch SMOKE ARM and SMOKE REFILL OFF 2 Circuit breaker PULL Page Date 31 October 2013 909 3 Section 909 Pilot s Operating Handbook Smoke System XTRA EXTRA 300L FIRE IN FLIGHT 1 Switch SMOKE ARM OFF CAUTION If the fire after the smoke system is shut off will not extinguish proceed as follows 2 Mixture IDLE CUT OFF 3 Fuel selector valve OFF Pull amp Turn 4 Master switch OFF 5 Airspeed 100 KIAS 185 km h find your airspeed attitude that will keep the fire away from the cockpit 6 Land AS SOON AS POSSIBLE 7 fire persists or aircraft is uncontrollable and wearing a parachute BAILOUT SMOKEIN THE COCKPIT 1 Switch SMOKE ARM OFF 2 Bad weather window OPEN 3 Ventilation OPEN 4 If smoke persists in the cockpit land AS SOON AS PRACTICAL 909 4 NORMALPROCEDURES The smoke system includes features for refilling the smoke tanks and smoke generation A REFILL A separate refill hose is delivered with the smoke system which has to be used for filling the smoke oil tanks from the paraffin oil supply cansister or barrel 1 Refill hose CONNECT hose nipple to quick connector at the fuselage bottom IMMERSE the other end into the paraffin oil in the canister barrel 2 Switch SMOKE REF
131. TERED IN BRAZIL 927 1 GENERAL This supplement is approved by the EASA on behalf of the Ag ncia Nacional de Avia o Civil ANAC for Brazilian registered aircraft in accordance with the Regulamento Brasileiro da Avia o Civil RBAC 21 Section 21 29 Theinformation contained within this supplementis to be used in conjunction with the basic AFM POH and supplements The information contained herein supplements or supersedes that in the basic manual and approved supplements only in those areas indicated Thefollowing POH AFM supplements are ANAC approved Section Title 901 Steerable Tail Wheel 902 Electric Pedal Adjustment 903 Electronic Accelerometer 904 Emergency Locator Transmitter 905 External Power 906 Digital RPM Indicator 907 Long Range Wing Tank Capacity 908 Airtow Hook 909 Smoke System 910 ACROIII Category 911 Single Seat Canopy 912 FILSER TRT 600 Transponder 913 FILSER TRT 800 Transponder 914 GARMIN GTX 327 Transponder 915 GARMIN GTX 330 Transponder 916 BENDIX KING KT 76A Transponder 917 BENDIX KING KT 73 Transponder 918 BECKER ATC 2000 Transponder 919 BECKER ATC 4401 Transponder 920 BECKER BXP 6401 Transponder 921 Lycoming AEIO 580 B1A Engine 922 Center Tank Increased Capacity 923 GARMIN GTX 328 Transponder 924 ASPEN EFD1000 PILOT PFD 925 GARMIN GNC 420W 926 ARTEXME 406 ELT 928 Landing Light Compliance with the limitations contained in the basic manual and approved supplements is
132. X 327 0 95 1 75 1 Transponder Garmin GTX 328 1 50 1 73 1 Transponder Garmin GTX 330 1 50 1 73 1 Transponder Becker BXP6401 1 0 80 1 60 1 Blind Encoder Module Becker BE 6400 01 0 10 1 39 A 1 Transponder Becker BXP6401 2 0 80 1 60 1 Blind Encoder Module Becker BE 6400 01 0 10 1 39 A 1 Transponder Becker ATC 2000 1 20 1 74 1 Transponder Becker ATC 4401 0 73 1 60 1 Transponder Antenna Comant Industries 105 0 11 0 14 1 Transponder Antenna Bendix King KA 60 0 11 0 14 1 Moba 210FA 0 10 4 38 R 1 COM Antenna Extra 83205A 0 10 4 38 A 1 COM Antenna Pointer P1 3001 10 0 05 4 38 A 1 Starter B amp C Speciality BC 315 100 2 4 63 0 85 R 1 Starter SKYTEC 149 12LS 3 65 0 85 A Lycoming 31A22 104 1 Alternator 60 Amps Electrosystems ALX 8421 LS 5 90 0 86 R with bracket 1 Voltage Regul Lamar B 00371 25 0 15 0 02 R 1 Low Volt Monitor Lamar B 00378 4 R 1 Alternator 65 Amps Bosch 0 120 489 935 4 60 0 86 A 1 Alternator 55 Amps Bosch 0 120 489 917 4 20 0 86 A 1 Alternator 55 Amps Bosch 0 120 489 469 4 20 0 86 A 1 Alternator 65 Amps Prestolite 66021637 4 70 0 86 A 6 14 Page Date 31 October 2013 Pilot s Operating Handbook XTRA Section 6 EXTRA 300L Weight and Balance and Equipment List QTY ITEM MANUFACT PART OR P N WEIGHT ARM MARKIF REQUIRED R kg m INSTALLED OPTIONAL O ALTERNAT A 1 Battery Sonnenschein Dryfit A 212
133. XTRA 300L To meet ICAO specifications the TRT 800 uses an external memory inside the aircraft connector housing of the cable set which is a part of the aircraft Because this cable is installed permanent into the aircraft a change of the transponder will not affect the aircraft address and the Flight ID In the event there is a Cradle error empty memory or data error OUT OF ORDER will be displayed The first line shows which kind of error is present Cradle OFF displayed means no or defective data Cradle Data displayed means digital checksum error After afew seconds the display shows normal operating condition but with inhibited Mode S The transponder will work with Mode A C only You will need to consult an authorized service station to enter the ICAO aircraft address see TRT800 Installation Manual Please consult your airworthiness authority for national procedures NOTE If no valid ICAO 24 bit aircraft address is programmed to the unit or if the memory is inoperative the transponder will inhibit the Mode S functions In this case only Mode A C function will be available 913 2 LIMITATIONS Not applicable 9133 EMERGENCY PROCEDURES The following emergency codes should be noted 7500 Hijacking 7600 Loss of communication 7700 Emergency 913 4 NORMAL PROCEDURES Not applicable 913 5 PERFORMANCE Not applicable 913 8 Page Date 15 December 2005 Pilot s Operating Handbook TR A EXTRA 300L
134. ability at any waypoint in the database if WAAS corrections are expected to be absent or disabled This AFMS does not constitute an operational approval for Oceanic or Remote area operations Additional equipment installations or operational approvals may be required 8 Oceanic navigation requires an additional approved long range oceanic and or remote area navigation system with independent display sensors antenna and power source b Operations approval may be granted for the use of the GNC 420W RAIM prediction function in lieu ofthe Prediction Program for operators requiring this capability Referto your appropriate civil aviation authorities for these authorizations 925 2 LIMITATIONS The system must utilize main software version 3 00 and GPS software version 3 0 or later FAA approved versions A valid and compatible database must be installed and contain current data The functionality of the GNC 420W be used for VFR navigation purposes only when areversion to traditional navigation map magnetic compass is possible at any time 925 2 1 PLACARDS GARMIN GNC420W GPS limited to VFR use only In the clear view of the pilot GPS Next to the GNC 420W circuit breaker 925 3 EMERGENCY ABNORMAL PROCEDURES 925 3 1 EMERGENCYPROCEDURES Notaffected 925 32 ABNORMAL PROCEDURES GPS NAVIGATION INFORMATION NOT AVAILABLE ORINVALID If GNC 420W GPS navigation information is not available or invalid utilize remaining operational
135. aced the main smoke oil tank which shuts the refill pump off An additional injection pump placed at the firewall within the engine compartment pumps the smoke oil from the floptube smoke oil tank through a solenoid valve and the injector nozzle into the hot exhaust gas to generate smoke The system consists of Main smoke oil tank with float switch Floptube smoke oil tank Refill pump in the pilot compartment with quick connector in the belly fairing njection pump in the engine compartment with a shut off solenoid in the pilot compartment switch on the throttle lever Two relais make contact type for pumps and for the solenoid control SMOKE ARM switch to arm the system and SMOKE REFILL switch for refilling placed at the instrument panel Circuit breaker for pumps and control placed at the instrument panel 0 o a soc 2 OC CONTROL lt BREAKER SINGLE PUMP SYSTEM A pump reversed polarity fills the floptube smoke oil tank through a quick connector located in the aircraft belly fairing This line includes a filter to prevent dirt to enter the smoke system The separate main smoke oil tank is finally filled through the interconnected floptube smoke oil tank Filled tanks are detected by a float switch placed in the main smoke oil tank which shuts the pump off The same pump
136. acity 9 US qt d Oil pressure Minimum Idling 172 kPa 25 Psi Normal 379 655 kPa 55 95 Psi Starting Warm up Taxi and Take Off 793 kPa 115 Psi CAUTION It is normal for the oil pressure to flicker from 10 to 30 psi 69 to 207 kPa when going from upright to inverted flight During knife edge flights and zero g flights oil pressure may drop and the oil system may not scavenge resulting in engine failure or damage if flight is prolonged Knife edge and zero g flight should not exceed 10 seconds WARNING If oil pressure drops to 0 psi kPa the propeller pitch changes automatically to coarse high pitch with a corresponding decrease in RPM Apply positive g to avoid engine stoppage e Fuel pressure Max 276 kPa 40 Psi Min 124 kPa 18 Psi Min Idle 83 kPa 12 Psi 2 4 Page Date 31 March 2009 Pilot s Operating Handbook Section 2 EXTRA 300L lt XTRA Limitations f Cylinder head temperature Max 260 C 500 2 5 PROPELLER MT Propeller Entwicklung GmbH Federal Republic of Germany a TypeMTV 14 B C C190 17 Maximum Take Off and Maximum Continuous 2700 rpm b Type 9 200 15 Maximum Take Off 5 min 2700 rpm Maximum Continuous 2400 rpm NOTE RPM limitation due to compliance with applicable noise protection requirements FAR 36 However for non US registered airplanes an enhanced rotational speed limitation of 2700 RPM may be permissable when registered in
137. ack code Aircraft is subject to unlawful interference 7600 Loss of communications 7700 Emergency 7777 Military interceptor operations Never squawk this code 0000 Military use Not enterable Changing the preset VFR code is done as follows Place the unit in SBY Select the desired VFR code While holding the IDT button in momentarily press the VFR button Avoid selecting code 7500 and all codes in the 7600 7777 range These trigger special indicators in automated facilities Only the code 7500 will be decoded as the hijack code An aircraft s transponder code if available is utilized to enhance the tracking capabilities of the ATC facility therefore care should be taken when making routine code changes 917 1 3 BUTTONS SELECTORS FOR OTHER 73 FUNCTIONS IDT Pressing the IDT Ident button while in the GND ON or ALT mode activates the Special Position Identification SPI Pulse for 18 seconds identifying your transponder return from others on the air traffic controllers screen The word will appear in the left lower corner of the altitude window while the IDT mode is active When the Function Selector Knob in test mode TST pressing the IDT button will return the brightness to the default factory value VFR Momentarily pressing the VFR Pushbutton sets the transponder code to the pre programmed VFR code superseding whatever code was previously entered Pressing the VFR key again and holding it for two seconds will
138. agneto systems Ignition Switch Tachometer Magneto Alert Indicator Lights Position LEFT Status LED RIGHT Status LED OFF ON ON RIGHT ON LEFT BOTH Between the left and right magneto ignition system alert indicators is a yellow RPM synchronization indicator This small yellow indicator is illuminated when there is a difference of more than 50 RPM between the right and left tachometers This indicator also may flicker during extreme RPM excursions of the engine OPERATION BUTTONS There are three panel buttons Each button has two modes of operation PRESS AND HOLD operation mode press and hold for more than 2 3 of a second Thisoperation mode is placarded above each button Hours Clear Trap Engine time Hours The left button upon depression will cause the tachometer to display the non fractional portion 0000 of the current accumulated engine hours When the button is released the fractional part of the engine hours 00 is displayed for a short period of time The clock is started whenever the engine RPM exceeds 800 RPM and is recorded in real hours Clear Clear The middle button clears the RPM trap During depression of the switch the RPM trap is zeroed When the button is released the trap will record the current engine RPM Engine RPM Trap The right button will cause the tachometer to display the current contents of the RPM trap This trap records the highest engine RPM achieved b
139. amp CENTER TANK Although safe operation does not require the use of the tanks in a specific sequence it is recommended to set fuel selector to amp CENTER TANK position 2 Empennage 1 All round inspection canopy surfaces stabilizers elevator trim tab rudder and tailwheel 2 Horizontal stabilizer attachment bols 3 Right Wing NOOR Aileron freedom of moveme Trailing edge Fuel tank vent opening right landing gear Fuel quantity Fuel tank filler cap Right landing gear wheel an Stall warning vane nt and security d brake CHECK CHECK FOR FREEPLAY BY MOVING THE TIP OF THE HORIZ STABILIZER UP AND DOWNWARDS CHECK CHECK CHECK CHECK CHECK CHECK CHECK Page Date 19 April 2012 ed Handbook R A Section 4 Normal Procedures 4 Nose Engine oil dipstick Propeller and spinner Air inlet Acro amp center fuel tank drain 5 Wing fuel tank drain 6 Fuelfilter drain 7 Exhaust silencer if installed 5 Left wing 1 Left landing gear wheel and brakes 2 Fuel quantity 3 Fuel tank filler cap 4 Pitot cover 5 Trailing edge 6 Aileron freedom of movement and security 6 Before starting engine Preflight inspection Passenger briefing Parachute handling briefing Seats seatbelts shoulder harnesses Canopy Brake Master switch Avionics power switch Electrical equipment 10 Alte
140. an alternative to the Lycoming AEIO 540 L1B5 engine the EXTRA 300L can be equipped with an AEIO 580 B1A engine It is a six cylinder horizontally opposed aircooled direct drive fuel injection engine with inverted oil system The EXTRA 300L with AEIO 580 B1A engine is available in one of the following fuel tank configurations ex factory both combined with a wing tank of 120 L 31 7 US gal capacity Configuration1 Acro and center tank with 51 L 13 4 US gal total fuel capacity refer to section 1 thru 7 of this handbook Configuration2 Acro and center tank with 69 L 18 2 US gal total fuel capacity The AEIO 580 B1A engine can be operated with the following propellers 1 Type MTV 9 B C C 200 15 3 blade constant speed 2 TypeMTV 14 B C C 190 17 4 blade constant speed 3 TypeMTV 9 B C C 198 25 3 blade constant speed 921 2 LIMITATIONS Thefollowing data deviate from the values given in Section 2 of this handbook 921 2 1 Engine Limitations a Rotational Speed Maximum Take Off and Maximum Continuous 2700 RPM NOTE Applicable RPM limitations approved for individual propeller types must be observed Refer to Section 2 5 eligible for the MTV 9 B C C 200 15 amp MTV 14 B C C 190 17 as well as Section 921 2 3 eligible forthe MTV 9 B C C 198 25 propeller b Fuel configuration 2 Total fuel capacity 189L 49 9 US gal Usable fuel capacity in the system 187L 49 4 US gal Acro amp Center Tank capacity 69L 18
141. an alternator failure and when the engine is not operating The battery is mounted behind the firewall All electrical circuits are protected by circuit breakers located on the rear instrument panel and they are easily accessible to the pilot during flight The electrical system is adequately suppressed to ensure satisfactory operation of the radio equipment All wires switches circuit breakers etc are manufactured to related aeronautical specifications Page Date 15 December 2005 7 13 Pilot s Operating Handbook Section 7 EXTRA 300L XTRA Description and Operation of Aircraft and Systems SHIVWES S3HDIIMS ONY uoydo Sd9 W0I uodo WO uoydg 5990 8 WOJ USONOdSNVUL Odd 553 QUE H sng YILSYW OIOV uodo 133208 uoydo OYAD J0NLILLY 173 m 5 sna WALSAS 3OWS 15 BNINSVM TIVIS sna m L NL ISH dL dv 311 4 69 uoydo VINI amp 1 15 lt 2 a 133308 OO 5534 10 uoidg N35 831340831330V NOLLV3UWN NWda3 JOVLIOA 53979 T3H 3801S AVN YOLVYNYAL TV WNHIDG UMOUS jueuudinb3 jeuondo pue WALSAS 1VOIHIOdI3 OILVIWN3HOS Page Date 08 October 2009 7 14 Pil
142. and plain grass runway the landing is increased by 15 OAT 0 C 32 F 15 C 59 F 30 86 F Landing Airspeed PA Land Land Land Land Land Land weight Roll over Roll over Roll over 15m 50 ft 15m 50 ft 15m 50 ft kg KIAS ft m m ft m ft m ft m ft m ft m ft Ibs km h 950 90 2095 167 2000 610 181 870 85 1918 157 2000 610 165 820 80 1809 148 2000 610 159 SL 171 561 527 1729 177 581 548 1798 185 607 586 1923 594 558 1831 188 617 580 1903 197 646 602 1975 4000 1219 192 630 592 1942 199 653 615 2018 208 682 639 2096 6000 1829 203 666 627 2057 211 692 652 2139 220 722 678 2224 SL 158 518 488 1601 164 538 507 1663 171 561 527 1729 541 518 1699 175 574 537 1762 181 594 558 1831 4000 1219 177 581 548 1798 185 607 570 1870 192 630 592 1942 6000 1829 188 617 582 1909 195 640 605 1985 203 666 627 2057 SL 150 492 465 1526 156 512 483 1585 163 535 502 1647 522 492 1614 166 545 511 1677 173 568 532 1745 4000 1219 168 551 522 1713 176 577 543 1781 184 604 565 1854 6000 1829 179 587 553 1814 186 610 575 1886 194 636 598 1962 Page Date 16 March 2009 Pilot s Operating Handbook XTRA EXTRA 300L Paragraph 6 1
143. ank intentionally 919 2 Page Date 15 December 2005 Pilot s Operating Handbook Section 919 EXTRA 300L BECKER 4401 Transponder 919 1 GENERAL The Becker panel mounted ATC 4401 Transponderis a radio transmitter and receiver that fulfills the role of the airborne beacon equipment according to the requirements of the Air Traffic Radar Beacon System ATCRBS Its functionality includes replying to ATCRBS Mode A and Mode C interrogations It operates on radar frequencies receiving ground radar interrogations at 1030 MHz and transmitting a coded response of pulses to ground based radar on a frequency of 1090 MHz The 4401 is equipped with IDENT capability that activates the Special Position Identification SPI pulse NOTE The ATC 4401 owner accepts all responsibility for obtaining the proper license before using the transponder Refer to Becker Pilot s Guide Page Date 15 December 2005 919 3 Section 919 Pilot s Operating Handbook BECKER 4401 Transponder XTRA EXTRA 300L 919 1 1 CONTROLS AND INDICATORS OFF SBY ON ALT OFF position Transponder is switched off rotary mode switch expect panel lighting A with 4 detent positions SBY position Standby mode is switched on ON position Mode is switched ALT position Mode is switched Rotary coding switch Control of the cursor in one of the 4 code digits or
144. antaneous Acceleration is 3g Therefore the middle LED and the first three positive LEDs are illuminated for the Instantaneous Accel eration Furthermore the ninth LED in positive direction is illuminated for the positive Current Extreme Value and the fifth LED in negative direction for the negative Current Extreme Value The LC Display shows 9 09 5 09 903 4 Page Date 20 April 2002 Pilot s Operating Handbook Section 903 EXTRA 300L X TRA Electronic Accelerometer After resetting the Current Extreme Values the LC Display shows A 3 0g 0 09 and only the middle LED and three LEDs in the positive range of the LED Display are shining If the display presents the Total Extreme Value you will see A 9 0g A 5 09 on LC Display because the Total Extreme Values has not changed The Total Extreme Values only change if one of them is lower than the corresponding Current Extreme Value or if they are reset to 0g ABSOLUTE EXTREME VALUES C Two further extreme acceleration values are the positive and the negative Absolute Extreme Value These values are the greatest acceleration values that ever occurred They can not be reset and they are stored in the long term memory inside the instrument Additionally time and date these Absolute Extreme Values occurred are stored These dates can be shown by the LC Display by pushing the buttons The Output of the Absolute Extrem
145. ar United Instruments UI8030 B 835 0 32 1 61 A 1 Airspeed Ind rear United Instruments UI8030 B 898 0 32 1 61 A dual scale 1 Airspeed Ind rear Mikrotechna Praha LUN 1106 K2B4 SC 0 50 1 61 A kts 1 Airspeed Ind rear Mikrotechna Praha LUN 1106 P2B4 SC 0 50 1 61 A km h 1 Vertical Speed Ind Winter 5 STVM 15 0 45 1 62 A metric 1 Vertical Speed Ind United Instruments UI7030M C 194 0 35 1 62 A metric 1 Vertical Speed Ind United Instruments UI7030 C 27 0 35 1 62 1 Vertical Speed Ind Mikrotechna Praha LUN 1144 8081 0 40 1 61 fpm 1 Vertical Speed Ind Mikrotechna Praha LUN 1144 2081 0 40 1 61 A m s 1 EGT CHT Westach 2 1 0 07 1 62 1 EGT Probe Westach 712 2 DWK 0 06 0 37 1 CHT Probe Westach 712 7 DK 0 05 0 20 1 EGT CHT Westach EF300 SC 2 DA 1 0 07 1 62 1 EGT Probe Westach 712 2 DWK 0 06 0 37 1 CHT Probe Westach 712 7 D 0 05 0 20 EGT CHT UMA D2 ET1K7K 0 07 1 62 A CT600J 01 1 EGT Probe UMA 2BU20 0 06 0 37 A 1 CHT Probe UMA 2B18 or 2B02 0 05 0 20 A 1 EGT CHT JPI EGT 701 0 41 1 56 6 EGT Probe JPI M 111 0 35 0 57 6 CHT Probe JPI M 113 S Plug Gask 0 26 0 56 1 OAT Probe JPI 400510 0 05 1 Oil Temp Probe 400500 L 0 05 0 22 1 Manifold Press Probe 604010 0 05 1 55 1 RPM Probe JPI 420815 1 0 05 0 11 1 Fuel Flow Transducer Flowscan 201 B or FXT 201 0 09 0 02 Shadin 680501 or 680600 0 09 0 02 A 1 Fuel Scan JPI FS 450 0 12 1 56 1 Fuel Flow Transdu
146. ation ALT Powers on the transponder in Mode A and Mode C At power on the last active identification code will be selected In ALT mode the transponder replies to identification and altitude interrogations as indicated by the Reply Symbol Replies to altitude interrogations include standard pressure altitude received from a separate encoder 915 1 2 CODE SELECTION Code selection is done with eight keys 0 7 that provide 4 096 active identification codes Pushing one of these keys begins the code selection sequence The new code will not be activated until the fourth digit is entered Pressing the CLR key will move the cursor back to the previous digit Pressing the CLR key when the cursor is on the first key of the code or pressing the CRSR key during code entry will remove the cursor and cancel data entry restoring the previous code You may press the CLR key up to five seconds after code entry is complete to return the cursor to the fourth digit The numbers 8 and 9 are not used for code entry only for entering a Count Down time contrast and display brightness and in the Configuration Mode IMPORTANT CODES 1200 The VFR code for any altitude in the US Refer to ICAO standards elsewhere 7000 The VFR code commonly used in Europe Refer to ICAO standards 7500 Hijack code Aircraft is subject to unlawful interference 7600 Loss of communications 7700 Emergency 7777 Military interceptor operations Never squawk this code 000
147. ax allowed empty weight Normal category 716kg 1578lbs PLACARD The existing FUEL SELECTOR VALVE placard has to be replaced by the following placard FUEL SELECTOR VALVE WING TANKS usable 154 L 40 7 US GAL in both cockpits near selector valve handle CENTER ACRO TANK usable 45 5 L 12 0 US GAL EMERGENCY PROCEDURES Not affected NORMAL PROCEDURES Not affected Page Date 20 April 2002 907 3 Section 907 Pilot s Operating Handbook Long Range Wing Tank Capacity XTRA EXTRA 907 5 PERFORMANCE RANGE ANDENDURACE Range and Endurance values for a T O Weight of 950 2095 Ibs including fuel for warm up and Take Off from SL max continuous Power climb to cruising altitude and a reserve of 21 litre 5 5 US Gal for 45 minutes with 4596 Power 5 5 liters 1 45 US Gal unusable fuel is taken into account At ISA Conditions PA Eng Manif Power Setting Fuel TAS IAS Endur Range Mixture Press Consumption ft m rpm inHg 96 hp L h gal h kts km h kts km h h nm km Best 2000 2700 27 4 95 285 88 2 610 2400 25 1 79 225 68 7 182 6 173 320 1 88 342 Power 2200 24 2 65 195 50 5 338 320 634 167 6 310 160 296 2 40 403 746 Power 159 3 295 152 282 3 27 520 964 278 267 259 248 964 Economy 2000 23 5 55 165 42 6 150 2 278 144 267 3 88 582 1078 Economy
148. cated sealed bearings 7 5 4 DIRECTIONAL FLIGHT CONTROL SYSTEM The dual rudder pedals with brake pedals are adjustable and operate the rudder through a cable system Springs keep the cables under tension when they are not operated 7 5 5 SECONDARY CONTROL The elevator trim control is located on the right side in the rear cockpit The canopy lock is operated from the outside by a handle on left side of the canopy by reaching into the cockpit through the window Inside a handle is located in both cockpits used for locking as well as for normal operation and for emergency release The starter magneto switch is located on the left side of the instrument panel in front of the rear seat Page Date 20 April 2002 7 5 Section 7 Pilot s Operating Handbook Description and Operation of Aircraft and Systems lt s X TRA EXTRA 300L 7 6 INSTRUMENTATION The Extra 300 L is equipped with flight instruments in both cockpits Instruments and placards can be provided with markings in either metric or English units The colour markings in instruments follow US FAR part 23 recommendation see section 2 7 6 1 INSTRUMENT PANEL REAR COCKPIT For instrument panel arrangement of the rear cockpit refer to Fig 7 6 1 which includes standard and optional equipment marked as such Fig 7 6 1 9 4 o o 5 5 5249 9 9 9 9 90
149. ccordance with ICAO Annex 16 as 77 3 dB A The noise level with propeller MTV 9 B C C200 15 has been established in accordance with FAR 36 Appendix G as 73 0 dB A No determination has been made by the EASA for the FAA that the noise levels of this airplane are or should be acceptable or unacceptable for operation at into or out any airport 2 14 Page Date 16 March 2009 Pilot s Operating Handbook XTR A EXTRA 300L Paragraph 3 0 3 0 1 3 0 2 3 1 3 2 3 2 1 3 2 2 3 2 3 3 2 4 3 2 5 3 3 3 3 1 3 3 2 3 4 3 4 1 3 4 2 3 4 3 3 5 3 5 1 3 6 3 7 3 8 3 9 SECTION 3 EMERGENCY PROCEDURES Table of Contents Page INTRODUCTION ec 3 3 elc 3 3 General Behaviour in Emeregency Situations 2 3 3 AIRSPEEDS FOR EMERGENCY OPERATION u u 3 4 OPERATIONAL CHECKLIST 3 4 Engine Failure during Take off sse nennen 3 4 Engine Failure immediately after 3 4 Engine Failure during Flight Restart Process 3 4 Oil System MalfUnctlOni oi irit as od gat cce irre vua cu se bee marie 3 5 Alternator ERE UE TRE NR REN 3 5 FORCED LANDINGS vu sisii 3 5 Emergency Landing without Engine 3 5 Precautionary Lan
150. cember 2008 Pilot s Operating Handbook Section 923 EXTRA 300L XTRA GARMIN GTX 328 Transponder Avoid selecting codes 0000 7500 and all codes in the 7600 7777 range These codes trigger special indicators in automated facilities An aircraft s transponder code is used for ATC tracking purposes therefore exercise care when making routine code changes 923 1 3 KEYS FOR OTHER GTX 328 FUNCTIONS IDENT Pressing the IDENT Key activates the Special Position Identification SPI Pulse for 18 seconds identifying your transponder return from others on the air traffic controller s screen The word IDENT will appear in the upper left corner of the display while the IDENT mode is active VFR Sets the transponder code to the pre programmed VFR code selected in Configuration Mode this is setto 7000 atthe factory Pressing the VFR Key again restores the previous identification code FUNC Changes the page shown on the right side ofthe display Display data includes Pressure Altitude Flight Time Count Up and Count Down timers Also displays Contrast and Display if manual control and backlighting is selected in the installation configuration START STOP Starts and stops the Count Up Count Down and Flight timers CRSR Initiates starting time entry for the Count Down timer and cancels transponder code entry CLR Resets the Count Up Count Down and Flight timers Cancels the previous keypress during code selection and Count D
151. cer Flowscan 201 B or FXT 201 0 09 0 02 Shadin 680501 or 680600 0 09 0 02 A 1 Manifold Press United Instruments UI6331 H 186 0 49 1 60 R Fuel Flow Ind 1 Manifold Press United Instruments UI6331 H 217 0 49 1 60 A Fuel Flow Ind 1 VHF Radio Becker AR 3201 0 90 1 54 R Page Date 31 October 2013 6 13 Section 6 XTRA Pilot s Operating Handbook Weight and Balance and Equipment List EXTRA 3001 QTY ITEM MANUFACT PART ORP N WEIGHT ARM_ MARKIF REQUIRED R kg m INSTALLED OPTIONAL O ALTERNAT A 1 VHF Radio Becker AR 4201 0 67 1 54 A 1 VHF Radio Becker AR 6201 0 85 1 54 A 8 33kHz ch spacing 1 VHF Radio Funkwerk ATR 833 0 60 1 55 A 8 33kHz ch spacing 1 Audio Panel Garmin GMA 240 0 68 1 49 1 Audio Panel Garmin GMA 340 0 80 1 49 A 1 GPS NAV COM Garmin GNS 430 2 95 1 49 1 GPS COM Garmin GNC 420W 2 65 1 49 A 1 GPS NAV COM Garmin GNS 430W 2 95 1 49 A 1 GPS NAV COM Garmin GNS 530W 3 75 1 49 A 1 Course Deviation Ind Garmin Mid Continent GI 102A 0 64 1 54 1 Course Deviation Ind Garmin Mid Continent GI 106A 0 64 1 54 A GPS Antenna Garmin AeroAntenna GA35 0 21 3 92 1 EFIS Aspen EFD1000PFD 1 31 1 60 1 Remote Sensor Module Aspen RSM 0 09 4 00 1 Transponder Bendix King KT 73 1 64 1 73 1 Transponder Bendix King KT 76A 0 89 1 75 1 Transponder Filser TRT 600 LAST 0 70 1 60 1 Transponder Filser TRT 800 0 70 1 60 1 Transponder Garmin GT
152. ciation presented below the aircraft symbol whenever the EFD1000 PILOT PFD is operating on the internal battery Will be accompanied by an indication of the estimated battery charge remaining Function FAIL Red annunciation presented whenever the EFD1000 PILOT PFD has determined that the associated function is invalid or failed and should not be used The data is removed from the display and replaced by a red X over the affected display feature CAUTIONS CROSS CHECK ATTITUDE Amber annunciation presented centered in the lower half of the attitude indicator whenever the EFD1000 AHRS internal integrity monitor determines that attitude is potentially degraded If a CROSS CHECKATTITUDE annunciation is provided the pilot should cross check attitude airspeed and altitude indications against real life horizon and the primary instruments GPS1 and or 924 10 Page Date 31 March 2009 Pilot s Operating Handbook Section 924 EXTRA 300L XTRA ASPEN EFD1000 PILOT PFD RSM GPS Amber annunciation presented on the left edge of the display to indicate when a configured GPS flight plan and mapping data is invalid or not available RSM GPS REVERSION EMER USE ONLY Amber annunciation presented on the bottom of the display whenever the EFD1000 PILOT PFD reverts to RSM GPS data and indicates that the RSM GPS is the current GPS source RSM GPS usage is limited to EMER GENCY USE ONLY ADVISORY Altitude aler
153. construction The dual chamber main spar fullfilling the requirement for fail safe design consists of carbon roving caps combined with CRP webs Core foam is a PVC foam Divinycell HT 50 The wing shell is built by a Honeycomb sandwich with CRP Laminates On the surface there is a protective layer of GRP To prevent buckling of the shell plywood ribs are used In the area of the wingtanks is a layer of CRP laminate with an incorporated aluminium thread bonded to the metal fuselage structure as means of lightning protection The connection to the fuselage is arranged by two bolts piercing through the spar parallel to the centerline of the fuselage and two brackets at the rear spars Integral fuel cells are provided in the leading edge of the wing extending from the root ribs to half the span of each R L and L H wing The ailerons are supported at three points in spherical bearings pressed into aluminium brackets To reduce pilot s hand forces the hinge line of the ailerons is positioned 25 of the aileron depth at the root and 21 5 at the tip Furthermore the ailerons are equipped with spades to decrease pilot forces Ailerons are controlled via the center bracket To prevent flutter the ailerons are weight balanced in the overhanging leading edge 7 4 EMPENNAGE The EXTRA 300 L possesses a cruziform empennage with stabilizers and moveable control surfaces The rudder is balanced aerodynamically at the tip Spars consist of PVC foam cores CRP ca
154. cted 910 4 NORMAL PROCEDURES AIRSPEEDS FOR NORMAL OPERATION CATEGORY ACRO I ACRO ACRO III NORMAL 1 seat 2 seats 2 seats KIAS km h KIAS km h KIAS km h KIAS km h Start Rotating Speed 65 120 Climb Vx 1 1 93 172 Vy 6 178 9 183 104 193 Recommended Normal Climb Speed 105 194 110 204 Max Cruise 185 343 185 343 185 343 Landing Approach 80 148 85 157 90 167 on Final 72 133 74 137 78 144 78 144 Go Around Speed 90 167 95 176 100 185 100 185 Recommended Airspeed For Flight In Rough Air max Va 158 293 158 293 158 293 140 259 Max Demonstrated Cross Wind Component 15 27 15kts 27 15 kts 27 15 kts 27 910 4 Page Date 16 March 2009 Pilot s Operating Handbook Section 910 EXTRA 300L X TRA Acro 111 Category 910 5 PERFORMANCE STALLSPEEDS CONDITION POWERIDLE FORWARD C G ANGLE OF BANK STALL SPEEDS WEIGHT CATEGORY 0 30 45 19 1 159 1 419 KIAS km h KIAS km h KIAS km h 950 kg Normal ACRO III 60 65 72 2095 Ibs 111 120 133 870 kg ACRO II 2 seat 57 61 68 1918 lbs 106 113 126 820 kg 1 seat 55 59 65 1808 Ibs 102 109 120 Max altitude loss during stall recovery is approximately 100 ft 30 m Page Date 16 March 2009 910 5 EXTRA 3001 Pilot s Operating Handbook XTRA WEIGHT AND BALANCE Section 910
155. ction 5 EXTRA 300L Performance 5 10 CRUISE PERFORMANCE Range and Endurance values for a T O Weight of 950 kg 2095 Ib including fuel for warm up and Take Off from SL max cont Power climb to cruising altitude and a reserve of 21 L 5 55 US gal for 45 minutes with 4596 Power 5 5 L 1 45 US gal unusable fuel is taken into account At ISA Conditions PA Eng Manif Power Setting Fuel TAS IAS Endur Range Mixture Press Consumption ft m rpm inHg 96 hp L h gal h kts km h kts km h h nm km Best 2000 2700 274 95 286 88 2 23 3 182 6 338 173 320 1 49 272 504 Power 610 2400 254 75 225 687 18 2 167 6 310 160 296 1 91 320 593 Power 2200 242 65 195 50 5 13 3 159 3 295 152 282 2 60 413 765 Economy 2000 23 5 55 165 42 6 11 3 150 2 278 144 267 3 08 462 856 Economy 2000 202 45 135 36 5 9 6 139 9 259 134 248 3 59 502 930 Economy 4000 2700 254 89 267 82 7 21 8 181 5 336 168 311 1 59 286 530 Power 1219 2400 246 75 225 687 18 2 170 9 317 158 293 1 91 324 600 Power 2200 237 65 195 50 5 13 3 162 4 301 150 278 2 59 418 774 Economy 2000 23 0 55 165 42 6 11 3 153 1 284 142 263 3 06 467 865 Economy 2000 19 7 45 135 365 9 6 142 6 264 133 246 3 59 507 9
156. ction 913 Pilot s Operating Handbook FILSER TRT 800 Transponder XTRA EXTRA 300L 7700 Emergency 7777 Military interceptor operations Never squawk this code 0000 Military use Not enterable Care should be taken not to select the code 7500 and all codes in the 7600 7777 range which trigger special indicators in automated facilities Only the code 7500 will be decoded as the hijack code An aircraft s transponder code if available is utilized to enhance the tracking capabilities of the ATC facility therefore care should be taken when making routine code changes STANDBY MODE The standby mode is activated by pressing the MODE button once This sets STBY in the mode indicator field The transponder will now only reply to direct addressed Mode S interogations The squitter stays active at a lower rate ALTITUDE OFF Switching off altitude reporting will be necessary if the ATC controller requests it For switching off altitude reporting the MODE button has to be pressed until A S is displayed The altitude display shows to indicate that the altitude reporting is not active Now the transponder will reply on Mode C interrogations with Mode C frames only and Mode S interrogations with 000 00008 instead of the actual altitude IDENT PressingtheIDT push button causes the special position identification pulse SPI to be appended to the Mode A replies for a period of 18 seconds and sets IDT in the
157. d the takeoff T O distance can be decreased by 5 For every 2 kts 4 km h tailwind up to 10 kts 19 km h the T O distance is increased by 1096 CAUTION All values are valid for single pilot air towing operation 820kg 1808 lbs TOW In case of an instruction flight with copilot the higher takeoff weight has to be considered The maximum permissible air towing speed of the glider needs to be observed Page Date 16 March 2009 908 5 EXTRA 3001 Pilot s Operating Handbook XTRA Section 908 Airtow Hook OSEE EZOT 02 929 Ev c 9 EZZ 698 SPZT ZES E881 v S 8867 6697 Qu 401 050 3 98 0 489 Do OZ COS 8272 cole 899 GOLT SES 7122 VEET sev 0902 829 29S OST 8S7 res zog lt ses 88ST ver sos eoe ssr 8SET Viv 960 698 soc 68cD SSE 282 Qu os Ww SL SL 4 01 050 3 98 0 489 Do 02 C voc ese 791 OLS 207 6 oes ver 698 781 906 9 2 922 699 voc 196 662 HLL
158. d airport then the desired procedure POWERING UP THE GNC 420W The GNC 420W power and COM volume are controlled using the power volume knob atthe top left corner of the unit Turning it clockwise will turn unit power on and increase the COM radio volume After turning the unit on a welcome pagewill be displayed while the unit performs a selftest followed bythe database confirmation pages which showthe current database information on the NavData card with the valid operating dates cycle number and database type indicated The database is updated every 28 days and must be current for instrument approach operations Information on database subscriptions is available inside your GNC 420W package To acknowledge the database information press ENT Page Date 31 March 2009 925 7 Section 925 Pilot s Operating Handbook GARMIN GNC 420W XTRA EXTRA 300L 925 7 2 DEFAULTNAV PAGE During mostflights the default NAV map and NAVCOM pages will be the primary pages used for navigation The default NA Vpagedisplays a graphic course deviation indicator CDI the active leg of your flight plan as defined by the current and to waypoints and six user selectable data fields The default settings for these fields are distance to waypoint DIS desired track DTK bearing to waypoint BRG ground speed GS ground track TRK and estimated time en route ETE The default NAV pageis selected by pressing and holding th
159. ded ERR 924 7 924 7 6 Setting Flight Instr rmerts ee 924 7 924 7 7 Syno aaa aa 924 8 924 7 8 ine ieee 924 8 924 7 9 Back Light Gonttol uk 924 9 924 7 10 924 10 924 7 11 Display Reversion Control and Abnormal 924 10 924 7 12 Warning Caution and Advisory 5 924 10 924 7 13 Ment RD 924 11 924 8 HANDLING SERVICING AND MAINTENANCE 924 12 Page Date 31 March 2009 924 1 Section 924 mE Pilot s Operating Handbook ASPENEFD1000PILOT PFD XTRA EXTRA 300L Left blank intentionally 924 2 Page Date 31 March 2009 Pilot s Operating Handbook 2 Section 924 EXTRA 300L XTRA ASPEN EFD1000 PILOT PFD 924 1 GENERAL The Aspen Avionics EFD1000 PILOT PFDisapanel mounted Electronic Flight Instrument System EFIS that presents the pilot with displays of attitude altitude indicated airspeed heading rate ofturn and slip skid information The system also displays supplemental flight data such as winds TAS OAT etc see Item 36 39 of Figure 1 pilot selectable indices bugs and various annuncia
160. ding with Engine Power sese eene 3 5 PIRES 3 6 DURING Starton Ground aa iad cerebri 3 6 lf Engine Falls to 3 6 Engin Frein FID 3 7 IGING 3 7 Inadvertent Encounter ectetur 3 7 NINTENTIONAL u I 122 3 7 MANUAL BAIL OUT 5 irren reinen iacu 3 7 EMERGENCY EXIT AFTER TURN OVER UU 3 8 ELEVATOR CONTROL FAILURE u u u tnn J J 3 8 Page Date 20 April 2002 3 1 Section 3 Pilot s Operating Handbook Emergency Procedures XTRA EXTRA 300L Left blank intentionally 322 Page Date 20 April 2002 Pilot s Operating Handbook Section 3 EXTRA 300L XTRA Emergency Procedures SECTION3 EMERGENCY PROCEDURES 3 0 INTRODUCTION 3 0 1 GENERAL This section contains the checklist and procedures coping with emergencies that may occur This checklist must be followed in various emergencies to ensure maximum safety for the crew and or aircraft Thorough knowledge of these procedures will enable the aircrew to better cope with an emergency The steps should be performed in the listed sequence However the procedures do not restrict t
161. div 0 30 1 60 A 1 Main Bus Fuseholder MTA 03 00360 0 03 0 02 1 Main Bus Strip Fuse 02 00300 40 Amps 1 PCB Auto Fuse EXTRA 83290 1 0 01 0 03 1 Fuel Cont Probe VDO 226 801 015 001 G 0 12 0 49 R Wing Tank 1 Fuel Cont Probe VDO 224 082 006 097 R 0 20 0 20 R Center Tank 42 L or 224 011 010 251 1 Fuel Cont Probe VDO 224 082 007 004 R 0 20 0 44 A Center Tank 60 L or 224 011 020 372 1 Fuel Cont Ind VDO 301 271 036 001 K 0 08 1 62 R Wing Tank or 301 030 001 G 1 Fuel Cont Ind VDO 301 272 052 001 K 0 14 1 62 R Acro Tank or 301 030 002 G 1 Ammeter VDO 190 004 039 002 0 08 1 62 R or 190 037 002 G 1 Volt Ammeter Electronics Intern VA 1A 0 26 1 62 A 1 Shunt Electronics Intern S 50 0 09 1 50 A 1 Volt Ammeter Electronics Intern VA 1A 50 0 22 1 62 A 1 RPM Indicator VDO 333 230 115 002 0 31 1 60 R or 333 035 001 G 1 RPM Indicatordigital Horizon P100 230 643 00 0 68 1 60 A 2700RPM 1 RPM Indicatordigital Horizon P100 230 635 00 0 68 1 60 A 2600RPM 1 Magnetic Compass Airpath C 2300 0 25 1 62 1 Magnetic Compass SIRS Navigation Ltd PG2A 0 13 1 62 Page Date 31 October 2013 Section 6 XTRA Pilot s Operating Handbook Weight and Balance and Equipment List EXTRA 3001 QTY ITEM MANUFACT PART OR P N WEIGHT MARKIF REQUIRED R kg m INSTALLED OPTIONAL O ALTERNAT A 1 Oil Press AMITEK or Christen 61943 0 51 1 62 R Oil
162. dress can be checked by pressing the push button FID The Flight Identification is displayed on the right side of the lower line By pressing the button FID for more than 3 seconds the input mode can be set or the Flight Identification can be changed FLAGS Squitter Flag When the extended squitter is active the letter S is displayed on the left top side of the display As the squitter is a periodic signal the displayed S is blinking Reply Flag In case of the transponder replying to interrogations the letter R is displayed on the left top side of the display 912 4 Page Date 15 December 2005 Pilot s Operating Handbook Section 912 EXTRA 300L XTRA FILSER TRT 600 Transponder In Flight Flag When there is an undercarriage switch installed the display can toggle between the letters F whether the aircraft is in flight condition or the letter G whether the aircraft is in condition The flag is displayed on the right bottom side of the display Battery Flag If the power supply to the transponder drops below 10 Volts the flag BAT appears and starts flashing 912 1 2 SYSTEM OPERATION The transponder should be turned off before starting and shutting down aircraft engines ON OFF After having switched on the AVIONIC MASTER switch the TRT 600 hasto be turned on by hand by pressing the ON OFF button forless then 1 second The display will first show the transponder type and the softwar
163. e It may be possible to minimize antenna shielding by locating the antenna where dead spots are only noticed during abnormal flight attitudes CAUTION The GTX 330 should be turned off before starting or shutting down aircraft engine The GTX 330 Transponder is automatically powered on by the respective AVIONIC MASTER switch or when previously manually powered off while AVIONIC MASTER switch is on by pressing the STBY ALT or ON keys After power on a start up page will be displayed while the unit performs a self test This supplementis written for software version 3 00 or later andis not suitable for earlier software versions Some differences in operation may be observed when comparing the information in this supplementto later software versions Verify the information herein with the GTX 330 pilot s guide PN 190 00207 00 applicable revision you received with yourtransponder Page Date 5 December 2008 915 3 Section 915 Pilot s Operating Handbook GARMIN GTX 330 Transponder XTRA EXTRA 300L 915 1 1 MODE SELECTION KEYS OFF Powers off the GTX 330 STBY Selects the standby mode displaying the last active identification code When in standby mode the transponder will not reply to any interrogations ON Selects Mode A At power on the last active identification code will be selected In this mode the transponder replies to interrogations as indicated by the Reply Symbol Replies do not include altitude inform
164. e CLR key orturning the small right knob 925 8 Page Date 31 March 2009 55 2719 Handbook SECTION 926 ARTEXME 406 ELT Table of Contents Paragraph Page 926 1 GENERA m 926 3 926 2 250 926 3 926 3 5 0 11 11111 11 926 4 926 4 NORMAL PROCEDURES U U u u 926 4 926 5 PERFORMANCE 2 I 926 4 926 6 WEIGHT amp CENTER OF GRAVITY u na ca a u uuu u uuu 926 4 926 7 SYSTEM DESCRIPTION 2 1 1 1 926 5 926 7 1 SWitcli re rere rn ee ua ta 926 5 926 7 2 TEST cire oce cie akana a eC 926 5 926 8 HANDLING SERVICING AND MAINTENANCE 926 6 926 8 1 Mio 926 6 926 8 2 SOLE MCSE u 926 6 Page Date 31 March 2009 926 1 Section 926 junii Pilot s Operating Handbook ARTEXME 406 ELT XTRA EXTRA 300L Left blank intentionally 926 2 Page Date 31 March 2009 Pilot s Operating Handbook
165. e Date 15 December 2005 918 5 Section 918 mE Pilot s Operating Handbook BECKER ATC 2000 Transponder XTRA EXTRA 300L 918 4 NORMAL PROCEDURES Not applicable 918 5 PERFORMANCE Not applicable 918 6 Page Date 15 December 2005 Pilot s Operating Handbook TR A EXTRA 300L Paragraph 919 1 919 1 1 919 1 2 919 1 3 919 1 4 919 1 5 919 1 6 919 1 7 919 1 8 919 2 919 3 919 3 1 919 4 919 5 SECTION 919 BECKER ATC 4401 TRANSPONDER Table of Contents Page GENERAD 919 3 Controls and 919 4 Switching on the unit pre flight 919 4 SOUAWK T eno 919 5 Flight operation in Mode A transponder reply code only 919 7 Flight operation in Mode reply code and altitude code 919 7 919 7 RW PEDE EET LL E 919 7 Gonfiguration 919 8 LIMITATIONS 919 8 5 919 8 MONTANE COGS c 919 8 NORMAL PROCEDURES Eoo 919 8 PERFORMANCE PG 919 8 Page Date 15 December 2005 919 1 Section 919 mE Pilot s Operating Handbook BECKER ATC 4401 Transponder XTRA EXTRA 300L Left bl
166. e Values is signed by a as first character of the two LC Display lines The Absolute Extreme Values only change if an Instantaneous Value occurs that is greater than the positive Absolute Extreme Value or lower than the negative Absolute Extreme Value TIME AND DATE You can recall the current time and date by pushing the buttons If you want to change the current time and date of the clock you have to enter the security code by the buttons In Case the code is wrong or you wait too long the instrument will return into the Normal Operating Mode The clock module has its own battery power supply backup preventing the clock from stopping even in case of turning off the master switch or disconnecting the DSA 12 from the electrical system of the aircraft Page Date 20 April 2002 903 5 Section 903 mE Pilot s Operating Handbook Electronic Accelerometer lt XTRA EXTRA 300L OPERATING INSTRUCTIONS The left button of the instrument will be called S1 and the right button will be called S2 during the following text If the LC Display shows acceleration values then the upper line exhibits the positive acceleration and the lower line shows the negative acceleration If the LC Display presents time and date you will see the time in the upper line and in the lower line you will see the date Button S1 LED Display 10 42 Button 52 DSA 12 2 ACCELEROMETER Contrast LC Display Bright 1 THE FI
167. e and firmware version To turn off the unit the button ON OFF must be pressed for more then two seconds or the AVIONIC MASTER switch must be placed to the OFF position ACS is the default operation mode and the transponder replies to Mode A C and S interrogations The pressure altitude will be displayed as Flight Level SQUAWK SELECTION Squawk selection is done with the four rotating knobs to provide 4096 identification codes The assignments of the knobs starting at top left are X selection of thousands 0 7 selection of hundreds 0 7 selection of ten 0 7 X selection of one 0 7 The code is entered in the lower line and remains inactive By pushing the UP AND DOWN ARROWS button the squawk code is transferred to the upper line and becomes active The code in the upper line is always the active one IMPORTANT CODES 1200 The VFR code for any altitude in the US Refer to ICAO standards elsewhere 7000 The VFR code commonly used in Europe Refer to ICAO standards 0021 The VFR code commonly used in Germany default is set to 0021 at time of installation 7500 Hijack code Aircraft is subject to unlawful interference 7600 Loss of communications 7700 Emergency Page Date 15 December 2005 912 5 Section 912 Pilot s Operating Handbook FILSER TRT 600 Transponder XTRA EXTRA 300L 7777 Military interceptor operations Never squawk this code 0000 Military use Not enterable Ca
168. e for earlier software versions This software version corresponds to the ASPEN Airplane Flight Manual Supplement Doc A 01 179 00 Revision C Some differences in operation may be observed when comparing the information in this supplement to later software versions Verify the information herein with the EFD1000 PILOT PFD Pilot s Guide Doc A 01 184 00 applicable Revision you received with your unit There you find also further information 924 2 LIMITATIONS The functionality ofthe EFD1000 PILOT PFD may be used for VFR navigation purposes only when areversion to traditional navigation map magnetic compass is possible at any time 924 2 1 PLACARDS ANDDECALS above the EFD display head For situational awareness only Next to the EFD1000 PILOT PFD circuit breaker Page Date 31 March 2009 924 3 Section 924 Pilot s Operating Handbook ASPENEFD1000PILOT PFD XTRA EXTRA 300L The following electronic placardis provided onthe EFD1000 PILOT PFD display wheneverthe RSM GPS is providing position data for the basemap display RSM GPS REVERSION EMER USE ONLY 924 3 EMERGENCY PROCEDURES Not affected due to the use as a secondary instrument 9244 NORMAL PROCEDURES Not affected due to the use as a secondary instrument 924 5 PERFORMANCE Not affected 9246 WEIGHT amp CENTER OF GRAVITY Refer to the equipment list in Section 6 of this Handbook 9247 SYSTEMDESCRIPTION 924 7 1 GENERAL The EF
169. e input COUNT UP TIMER The count up timer is controlled by the START STOP and CLR keys Pressing the CLR key zeros the display COUNT DOWN The count down timer is controlled by START STOP CLR and CRSR keys The initial Count Down timeis entered with the 0 9 keys Pressing the CLR key resets thetimer to the initial value STBY The transponder will not reply to any interrogations GND This page is not active CONTRAST This page is only displayed if manual contrast mode is selected in Configuration Mode Contrast is controlled by the 8 and 9 keys DISPLAY This page is only displayed if manual backlighting mode is selected on Configuration Mode Backlighting is controlled by the 8 and 9 keys 915 1 5 CONFIGURATION MODE The configuration is normally set at time of installation including the unique Mode S aircraft address The configuration Mode should not be used during flight Refer to the GTX 330 pilot s guide PN 190 00207 00 applicable revision you received with yourtransponder 915 1 6 ALTITUDE TRENDINDICATOR When the PRESSURE is displayed an arrow is displayed to the right of the altitude indicating that the altitude is increasing or decreasing One of two sizes of arrows is displayed depending on the rate of climb amp descent The sensitivity of these arrows is set using the Configuration Mode vertical speed rate 915 1 7 FAILUREANNUNCIATION If the unit detects an internal
170. e key position with exception of panel lighting SBY Transmitter tube warm up ON Transponder responds to mode A interrogation with the set code ALT Transponder responds to mode and mode C interrogation TEST Built in test by interrogation simulation REPLY lamp must light up IDENT button Pushbutton Pressing the IDENT button the transponder transmits an SPI pulse REPLY lamp Lamp orange with dimmer Lights up if transponder responds intensity set by means of a mechanical dimmer 4 coding switches Rotary switches with eight Setting the code from 0000 to 7777 permitting positions 4096 different digit combinations Code readout Digital readout each digit Indication of coding from 0000 to 7777 from 0 to 7 Page Date 15 December 2005 918 3 Section 918 Pilot s Operating Handbook BECKER 2000 Transponder XTRA EXTRA 300L NOTE The ATC 2000 owner accepts all responsibility for obtaining the proper license before using the transponder Caution Do not switch on or off the transponder until the engines have been startet or stopped respectively to avoid damage to the transponder due to current surges 918 1 1 BUILT IN TEST 1 Position mode switch from OFF to SBY Operate the transponder approx 60s in the SBY position since transmitting tube must warm up and stabilize prior to operation It is however possible to skip the SBY position without danger for the transmitte
171. e mechanism is a typ E 85 of the TOST company Munich It is mounted at the tail spring rear end aft the tail wheel and activated with a yellow handle located at the rear seat cockpit via a bowden cable 908 8 HANDLING SERVICING AND MAINTENANCE Service and maintenance needs to be conducted in accordance with the latest operation handbook Typ E 85 of the manufacturer TOST GmbH Germany Additionally during the 100 h inspection the bowden cable and the release handle have to be checked 908 8 Page Date 16 March 2009 Handbook XTR A SECTION 909 SMOKE SYSTEM Table of Contents Paragraph Page 909 1 GENERAL uuu aa sas kaa qu amu ass 909 3 909 2 LIMITATIONS u 909 3 909 3 EMERGENCY PROCEDURES 909 3 909 4 NORMAL PROCEDURES aux mln sucus 909 4 909 5 PERFORMANCE uuu i 909 5 909 6 WEIGHT AND BALANCE 909 5 909 7 DESCRIPTION OF THE SYSTEM kan annuum nauim 909 5 909 8 HANDLING SERVICING AND MAINTENANCE 909 7 Page Date 20 September 2006 909 1 Section 909 junii Pilot s Operating Handbook Smoke System XTRA EXTRA 300L Left blank intentionall
172. e right side of the fuselage A torque tube connects the valve to both cockpit handles Pull and turn the handle 90 to open the valve to the Acro amp Center tank A further 90 turn switches to the Wing tank fuel supply Position down CLOSED Position ACRO amp CENTER TANK Position WINGTANK 7 10 9 EXHAUST SYSTEMS OPTIONAL Optionally the EA 300 L can be equipped with an additional silencer system type Gomolzig The attachment is integrated in the fuselage structure Thus no modifications are necessary to install the silencer system Alternatively a complete 6 in 1 System with integrated silencer is available 7 11 FUEL SYSTEM The fuel system consists of two separate independent tanks Acro amp center tank in the fuselage Wing tank LH and RH Wing tank The root section of each wing in front of main spars forms an integral fuel tank providing two interconnected tanks with 120 liters 31 7 US GAL total capacity Each side of the wing has a 2 diameter filler cap for gravity refueling The wing tank can be completely emptied in flight Acro amp center tank An Acro tank 9 liters 2 3 US Gal is mounted in the fuselage just behind the firewall and the Center tank 42 liters 11 1US Gal in front of the main spar of the wing The Acro tank is connected with the center tank in a gravity feed system The center tank has a 2 diameter filler cap for gravity refueling Unusable fuel is approximately 5 5 lit
173. ection 917 EXTRA 300L XTRA BENDIX KING KT 73 Transponder 917 1 7 FAILURE ANNUNCIATION If the unit detects an internal failure FAIL annunciation light on the left side of the displays will illuminate 917 2 LIMITATIONS Not applicable 917 3 EMERGENCY PROCEDURES IMPORTANT CODES 7600 Loss of communications 7500 Hijacking 7700 Emergency All secondary surveillance radar sites are ready to receive this code at all times See the Airman s Information Manual AIM for a detailed explanation of identification codes 917 4 NORMAL PROCEDURES Not applicable 917 5 PERFORMANCE Not applicable Page Date 31 March 2009 917 7 Section 917 mE Pilot s Operating Handbook BENDIX KING KT 73 Transponder XTRA EXTRA 300L Left blank intentionally 917 8 Page Date 31 March 2009 Pilot s Operating Handbook TR A EXTRA 300L Paragraph 918 1 918 1 1 918 1 2 918 1 3 918 1 4 918 2 918 3 918 3 1 918 4 918 5 SECTION 918 BECKER ATC 2000 TRANSPONDER Table of Contents Page GENERAL u 918 3 TOS 918 4 Squawk selection uk u inin aa 918 4 Mod Operations quan 918 5 Mode and C 918 5 LIMITATIONS
174. ed at the transponder 1 ThelBIT Initiated Built in Test can be activated in any mode excluding the configuration mode with the push of F and atthe same time The action starts with the leading edge ofthe second pushed button The IBIT works as follows in all modes Thetest starts with all available test routines including the transmitter test routine During the test IBIT is indicated on the display The test takes not longer than 1 second If the IBIT was successful the XPDR switches immediately into the normal operating mode During the IBIT any action from other switches is not recognized Negative results of the are indicated on the display with FAILURE The transponder may be not switched into ON or ALT mode if any failure was found 2 The Continuous Built in Test works as follows Thecontinuous BIT acts as a kind of watchdog during operation Negative results ofthe CBIT are indicated on the display with FAILURE In this case the transponder may be not switched into ON ALT mode display indication of operating mode set to SBY if any failure was found 3 The PBIT Power on Built in Test works as follows The XPDR has apower on after switching on During the PBIT any action from other switches are not accepted 920 6 Page Date 31 March 2009 Pilot s Operating Handbook Section 920 EXTRA 300L XTRA BECKER BXP 6401 Transponder During PBIT the XPDR is in the SBY mode bu
175. ed the structural capability of the aircraft CAUTION both cockpits Particular caution must be exercised when performing maneuvers at speeds above V 293 km h Large or abrupt control inputs above this speed impose unacceptably high loads which exceed structural capability of the aircraft WARNING SOLO FLYING FROM REARSEATONLY on front instrument panel Page Date 16 March 2009 Section 2 Limitations XTRA 2143 INSTRUMENT MARKINGS AIRSPEED INDICATOR greenarc yellow arc redline OIL PRESSURE INDICATOR 60 KIAS 111 km h 158 KIAS 293 km h 158 KIAS 293 km h 220 KIAS 407 km h 220 KIAS 407 km h Range markings are depending on instrument installed redline yellow arc green arc yellow arc redline 25 Psi 25 Psi 55 Psi 55 Psi 90 Psi or 55 95 Psi 90 Psi 100Psi or 95 115 Psi 100 Psi 115 Psi OIL TEMPERATURE INDICATOR yellow arc green arc yellow arc red line lt 140 F 140 F 210 F 210 F 245 F 245 F CYLINDERHEAD TEMPERATURE INDICATOR yellow arc green arc yellow arc red line RPM INDICATOR green arc yellow arc red line G METER green arc yellow arc red line FUEL FLOW INDICATOR green arc redradial Refer to Section 4 6 and 4 8 2 lt 150 F 150 F 435 F 435 F 500 F 500 F 700 RPM 2400 RPM 2400 RPM 2700 RPM 2700 RPM 5g 80 89
176. edures lt s XTRA EXTRA 300L 4 12 ACROBATIC MANEUVERS 4 42 1 GENERAL NOTE Prior to executing these maneuvers tighten harnesses and check all loose items are stowed Start the maneuvers at safe altitude and maximum continuous power setting if not otherwise noted For maneuver limits refer to Section 2 LIMITATIONS After termination of acrobatic maneuvers the artificial horizon if installed must be reset if possible At high negative g loads and zero g periods it is normal that oil pressure and RPM indication might drop down momentarily returning to normal status at positive g loads The high permissible load factors oftheairplane may exceed the individual physiological limits of pilot or passenger This fact must be considered when pulling or pushing high g s 4 12 2 MANEUVERS CAUTION Particular caution must be exercised when performing maneuvers at speeds above V 158 KIAS 293 km h Large or abrupt control inputs above this speed may impose unacceptably high loads which exceed the structural capability of the aircraft Acrobatics is traditionally understood as maneuvers like loop humpty bump hammerhead turn aileron roll etc This manual does not undertake to teach acrobatics however it is meant to demonstrate the plane s capabilities For this reason maneuvers are divided into segments The segments are described Limitations are pointed out Segment horizontal line A horiz
177. efore the button was pressed Page Date 19 April 2012 906 5 Section 906 Pilot s Operating Handbook Digital RPM Indicator XTRA EXTRA 300L 906 8 PRESS AND RELEASE operation mode press and release in less than 2 3 of a second This operation mode is placarded below each button L DIM Masks R During normal operation the tachometer presents the average of the left and right internal tachometers on the display However a mechanism exists to mask either tachometer from the display leaving the remaining tachometer to determine magneto ignition problems Quickly pressing and releasing the left button L causes the tachometer to mask the left tachometer Quickly pressing and releasing the right button H causes the tachometer to mask the righttachometer Dimmer DIM Quickly pressing and releasing the middle button DIM causes the tachometer to alternately dim or brighten the LED indicators except the large red LED of the RPM Range HANDLING SERVICING AND MAINTENANCE Not affected 906 6 Page Date 19 April 2012 XTR A SECTION 907 LONGRANGE WING TANK CAPACITY Table of Contents Paragraph Page 907 1 907 3 907 2 E rye cpm 907 3 907 3 EMERGENCY eene ence nean ates nea sas a 907 3 907 4 NORMAL PROCEDURES
178. eight 701 kg 1546 Ibs 665 kg 1466 Ibs Min Air Towing Speed 66 KIAS 122 km h 68 KIAS 126 km h Best Air Towing Speed 72 76 KIAS 74 78 KIAS 133 141 km h 137 144 km h NOTE 2 seats only in case of an instruction flight 1 Maximum air towing speed 2 maximum permissible air towing speed of the glider 2 The maximum permissible cylinder head temperature is 500 F red line 3 Interior mirror mounted For the location of the yellow release knob the following placard has to be attached in the near of the knob Page Date 16 March 2009 908 3 XTR A Pilots Operating EMERGENCY PROCEDURES A ABORTED TAKE OFF 1 Pilot of the glider INFORM 2 Throttle IDLE 3 Mixture IDLE CUT OF 4 Brakes APPLY AS PRACTICAL B ENGINE FAILURE IMMEDIATELY AFTER TAKEOFF Stall speed 60 KIAS 111 km h 1 Pilot of the glider INFORM 2 Air tow RELEASE 3 Airspeed 80 KIAS 148 km h 4 Mixture IDLECUTOFF 5 Fuelshutoff valve OFF 6 Ignition switch OFF 7 Master switch OFF 8 Forced landing PERFORMAS PRACTICAL C EXCESSIVE CLIMB OVER BY THE TOWING GLIDER 1 Pilot of the glider INFORM 2 Air tow RELEASE 3 Landing PERFORM AS PRACTICAL D TOW BREAK 1 Pilot of the glider INFORM 2 Landing PERFORM AS PRACTICAL NORMAL PROCEDURES Preflight inspection starting procedures take off procedure and the following climbing flight have to be carry out in accordance with C
179. elf contains also the release mechanic which gives the wheelfork a full swivel capability exceeding plus minus 30 deflection The steelsleeve is glued into the glasfiberspring which is bolted to the tail hardpoint of the aircraft The steering of the tailwheel is accomplished by a direct mechanic link rudder control cable from the rudder pedals The steering deflection of the tailwheel is controlled by the rudder movement and dampened by anti shimmy connector springs Page Date 20 April 2002 901 3 Section 901 Pilot s Operating Handbook Steerable Tail Wheel XTRA EXTRA 300L 901 8 HANDLING SERVICING AND MAINTENANCE During 50 hour inspection the bearing steelsleeve has to be lubricated on the point of lubricating Additionally all parts of the tailwheel have to be inspected visually for deforma tions cracks and corrosion 901 4 Page Date 20 April 2002 2 Handbook XTR A SECTION 902 ELECTRIC PEDAL ADJUSTMENT Table of Contents Paragraph Page 902 1 GENERAL 2 P 902 3 902 2 5 902 3 902 3 EMERGENCY PROCEDURES a aix d nana 220 902 3 902 4 NORMAL PROCEDURES III UU 902 3 902 5 PERFORMANCE u 902 3 902 6 WEIGHT AND BALANCE 4 2 001 11 22 aS
180. er Call Sign The indication of Al in the bottom line of the display is in mode SBY and ON only if selected in configuration menu The Aircraft Identifier fixed is available in any mode after pressing SEL button G and turning the rotary encoder B The default value for Al is the Tail Number of the aircraft and is stored in the Address Module If a flight plan exists it has to be checked which Al has to be used If a Flight Number is assigned it has to be entered If a Company Call Sign is mentioned this has to be entered To enter it see below It willbe stored in the EEPROM ofthe control head In this case the indication the display changes to FN Flight Number If the Call Sign Tail Number is mentioned no change as it is the default setting from the Address Module Page Date 31 March 2009 920 7 Section 920 Pilot s Operating Handbook BECKER BXP 6401 Transponder XTRA EXTRA 300L SETTING THE FLIGHT NUMBER 1 2 Press SEL button G to enter the select mode Rotate B until is displayed Push C to switch to FN The cursor is set on the first character Rotate B to change this character Push C to set the cursor to the next character Repeat steps 4 and 5 until the flight number is entered If the flight number consists of less than 7 characters put a space at the end to fill the remaining characters with spaces Store the changes with STO button F For leaving the setting
181. erating Handbook EXTRA 300L XTRA RATEOF CLIMB PERFORMANCE 5 6 uu 04 94D SVM 6 56 86 281 61 101 1 4 sq r921 91 08 4 008 098 00 2 0082 002 u1Uu 3J 6861 26002 006 056 4 9 3 814 2 00 50 5 017 851 851 851 851 4 8 4 9 851 1300091 3200071 1300021 1300001 140008 140009 130007 110002 IS 3NI unu 029 OZET 951 0008 VSI 0002 641 7 81 9M 098 LHOIS3M 2OM Wd 01 vl 208 Page Date 16 March 2009 Pilot s Operating Handbook Section 5 EXTRA 300L XTRA Performance TIME TO CLIMB FUEL TO CLIMB 5 7 1 9 5 186 99 076 691 0 687 608 9861 220281 3 1 2101 8 9 v 0 056 006 FHP r OL 7303 pe np gv 7303 OL 750 0008 lt YSI 0002 S81 7281 098 728 7921 058 008 OSL 004 VSI GaadS AA H3MOd LNOO 02 SNOILIGNOOD ulu 3 841129 01 AWIL Page Date 20 April 2002 5 10 Section 5 Performance Pilot s Operating Handbook EXTRA 300L XTRA RANGEANDENDURANCE 5 8 SuH S
182. erconnected tanks with 154 litres 40 7 US GAL total capacity Each side of the wing has a 2 diameter filler cap for gravity refuelling The long range tank has two compartments in either wing which are separated by a slosh rib Due to the interconnection the fuel level of the left and right integral tank will equalize during refuelling within reasonable time For max fuel capacity the first filled side has to be filled once again The wing tank can be completely emptied in flight 907 8 HANDLING SERVICING AND MAINTENANCE Not affected 907 6 Page Date 16 March 2009 A Handbook SECTION 908 AIRTOW HOOK Table of Contents Paragraph Page 908 1 GENERAL 908 3 908 2 LIMITATIONS 908 3 908 3 EMERGENCY PROCEDURES 908 4 908 4 NORMAL PROCEDURES urne rni na erra anc a a uma EE Ra 908 4 908 5 dsiuellnUIed 908 5 908 6 WEIGHT AND BALANCE uuu x an 908 7 908 7 DESCRIPTION OF THE SYSTEM nnne knee anam aem 908 7 908 8 HANDLING SERVICING AND MAINTENANCE 4 4 222211 908 7 Page Date 20 April 2002 908 1 Section 908 junii
183. ered on by the respective AVIONIC MASTER switch or when previously manually powered off while AVIONIC MASTER switch is on by pressing the STBY ALT or ON keys After power on a start up page will be displayed while the unit performs a self test This supplementis written for software version 5 00 or later andis not suitable for earlier software versions Some differences in operation may be observed when comparing the information in this supplementto later software versions Verify the information herein with the GTX 328 pilot s guide PN 190 00420 03 applicable revision you received with your transponder There you find also further information Page Date 5 December 2008 923 3 Section 923 Pilot s Operating Handbook GARMIN GTX 328 Transponder XTRA EXTRA 300L 923 1 1 MODE SELECTION KEYS OFF Powers off the GTX 328 Pressing STBY ONor ALT Key powers on the transponder displaying the last active identification code STBY Selects the standby mode When in standby mode the transponder will not reply to any inter rogations ON Selects Mode A In this mode the transponder replies to interrogations as indicated by the Reply Symbol Replies do not include altitude information ALT Selects Mode A and Mode C In ALT mode the transponder replies to identification and altitude interrogations as indicated by the Reply Symbol Replies to altitude interrogations include the standard pressure altitude received from a
184. erformed the default display of the engine RPM appears on the display The default display is insured via the use of internal timers that will restore the display to the current RPM even in the event that one of the panel buttons becomes stuck or defective Internally two independent tachometers watch the pulses received from each magneto Each tachometer is accurate to less than 1 RPM and can be individually enabled disabled via buttons on the face of the indicator RPMrange C Magneto Control RPM restriction Operation placard Press and hold Operation placard Press and release 906 4 Page Date 19 April 2012 Pilot s Operating Handbook Section 906 EXTRA 300L XTRA Digital RPM Indicator RPM RANGES Engine operating ranges are indicated by the large green yellow and red LEDs These LEDs are located on the upper right corner of the indicator face MAGNETO CHECK Three small LED magneto system alert indicator lights are located within the Status aera on the upper left corner of the indicator face The left and right red LED alert indicator lights when illuminated indicate because of loss of ignition signal to the tachometer a possible malfunction of the respective left or right magneto ignition system While performing a magneto check during engine run up the red alert indicator lights will illuminate thus identifying the grounding of the respective right or left m
185. ers 1 45 US Gal Adequate venting is provided in each tank to a main ventilation tube ending outside the fuselage at the right side In addition to the engine driven fuelpump an electrically driven auxiliary fuel pump boost pump with by pass and having sufficient capacity to feed the engine at take off power is fitted as a safety device against failure of the engine driven pump The boost pump switch is located on the instrument panel 7 12 Page Date 15 December 2005 Pilot s Operating Handbook Section 7 EXTRA 300L X TRA Description and Operation of Aircraft and Systems A fuel filter with drain is installed between the fuel selector valve and the boost pump Separate drains are located at the lowest point of each tank system Normal float type transducers and electrically operated fuel indicators are used 7 12 ELECTRICAL SYSTEM The electrical system is supplied by a 12 V alternator with rectifier transistor voltage regulator The alternator is mounted on and driven by the engine The field current is controlled by the voltage regulator to nominal 14 V under all load conditions The masterswitch is located on the rear instrument panel Circuit protection against overvoltage is provided by the voltage regulator The maximum load taken from the alternator is 40 amp A 12 V leak proof battery is connected across the alternator output to stabilize the supply and to maintain all essential services in the event of
186. essing the CLR key resets the timer to the initial value STBY The transponder will not reply to any interrogations GND This page is not active CONTRAST This page is only displayed if manual contrast mode is selected during installation configuration Contrast is controlled by the 8 and 9 keys DISPLAY This page is only displayed if manual backlighting mode is selected during installation configuration Backlighting is controlled by the 8 and 9 keys 923 1 5 CONFIGURATION MODE The configurartion mode is not active The GTX 328 s options are normally setat time of installation To request any changes of the GTX 328 parameters contact an authorized Garmin Aviation Service Center 923 1 6 ALTITUDE TRENDINDICATOR When the PRESSURE ALT page is displayed an arrow may be displayed to the right of the altitude indicating thatthe altitude is increasing or decreasing One of two sizes of arrows may be displayed depending on the vertical speed rate The sensitivity of these arrows is set by an authorized Garmin Aviation Service Center 923 1 7 FAILURE ANNUNCIATION If the unit detects an internal failure the screen displays FAIL When FAIL is annunciated no transponder data is transmitted 923 6 Page Date 5 December 2008 Pilot s Operating Handbook Section 923 EXTRA 300L XTRA GARMIN GTX 328 Transponder 923 2 LIMITATIONS Notapplicable 923 3 EMERGENCY PROCEDURES 923 3 1 IMPORTANT C
187. est only To enshure instant readiness position the mode switch to SBY standby during the flight Set the code requested by ATC using the four coding switches Set two digit code numbers in the first two windows of the readout Caution Only operate the coding switches in the SBY standby mode 3 Switch the mode switch ON on ATC request the transponder then responding to mode A interrogation with dialed code as indicated by the REPLY lamp coming on Only press the IDENT button briefly when requested by ATC causing a special identification pulse SPI pulse being transmitted permitting instant identification of the aircraft on the ATC radar system 918 1 4 MODE A AND C OPERATION 918 2 918 3 918 3 1 1 Postion mode switch to ALT on ATC request only The transponder then responds with dialed code causing REPLY lamp to light up and additionally transmits the height of the aircraft to ATC 2 Press the IDENT button briefly when requested by causing a special identification pulse SPI pulse being transmitted permitting instant identification of the aircraft on the ATC radar system LIMITATIONS Not applicable EMERGENCY PROCEDURES IMPORTANT CODES 7600 Loss of communications 7500 Hijacking 7700 Emergency All secondary surveillance radar sites are ready to receive this code at all times See the Airman s Information Manual AIM for a detailed explanation of identification codes Pag
188. from the display field B with 8 detents positions continuously rotable Rotary coding switch Setting the code digits from 0 to 7 C with 8 detents positions continuously rotable Ident push button In Mode A and Mode A C this triggers the transmission of an D IDT identification impulse additional to the Mode A reply code for approx 18 seconds During this time appears in the bottom line of the LC display E 2 line LC display Code indication top line Codes from 0000 to 7777 are possible Mode indication bottom line SBY mode SbY is displayed Mode ON appears in the display is displayed the duration of the identification function Mode A C a valid altitude is present the flight level height in steps of 100 ft preceded by F e g F241 24100 ft appears If no valid altitude code is present is diplayed The flight level display can be switched off in the configuration mode is displayed for the duration of the identification function F Code push button Activates a first user specific code VFR1 G Code push button Activates a second user specific VFR code VFR2 H Reply indication The triangle signals a Transponder reply REPLY J Store push button Stores user specific VFR codes or changes in STO the configuration mode 919 1 2 SWITCHING ON THE UNIT PRE FLIGHT CHECK 1 Check that the circuit breaker is set and switch on the aircraft power supply CAUTION Do
189. ft a change of the transponder will not affect the aircraft address and the Flight ID In the event there is a Cradle error empty memory or data error OF ORDER will be displayed The first line shows which kind of error is present Cradle OFF displayed means no or defective data Cradle Data displayed means digital checksum error After afew seconds the display shows normal operating condition but with inhibited Mode S The transponder will work with Mode A C only You will need to consult an authorized service station to enter the ICAO aircraft address see TRT 600 Installation Manual Please consult your airworthiness authority for national procedures NOTE If no valid ICAO 24 bit aircraft address is programmed to the unit or if the memory is inoperative the transponder will inhibit the Mode S functions In this case only Mode A C function will be available 912 2 LIMITATIONS Not applicable 912 3 EMERGENCY PROCEDURES The following emergency codes should be noted 7500 Hijacking 7600 Loss of communication 7700 Emergency 912 4 NORMAL PROCEDURES Not applicable 912 5 PERFORMANCE Not applicable 912 8 Page Date 15 December 2005 Pilot s Operating Handbook TR A EXTRA 300L Paragraph 913 1 913 1 1 913 1 2 913 1 3 913 2 913 3 913 4 913 5 SECTION 913 FILSER TRT 800 TRANSPONDER Table of Contents Page GENERAL
190. ft can be flown only with the pilot in the rear seat EMERGENCY PROCEDURES Not affected NORMAL PROCEDURES Befor starting engine check front seat area and ensure seat belts and shoulder harness of front seat are completely removed or fastened and secured so that nothing can obstruct the free movementof controls PERFORMANCE Not affected WEIGHT AND BALANCE AND EQUIPMENT LIST Refer to the equipment list in section 6 DESCRIPTION OF THE SYSTEM The single seat canopy has been designed to easily replace the standard canopy This can be achieved by using the same canopy frame hinges and latches included The front seat is covered by the flat portion of the frame in front of the canopy Operation of the locking mechanism is feasible only from the rear seat HANDLING SERVICE AND MAINTENANCE Not affected Page Date 31 March 2009 911 3 Section 911 Pilot s Operating Handbook Single Seat Canopy XTRA EXTRA 300L Left blank intentionally 911 4 Page Date 20 April 2002 Pilot s Operating Handbook TR A EXTRA 300L Paragraph 912 1 912 1 1 912 1 2 912 1 3 912 2 912 3 912 4 912 5 SECTION 912 FILSER TRT 600 TRANSPONDER Table of Contents Page GENERAL 912 3 Front Panel 912 3 System E 912 5 Error Reporting Fault
191. g Handbook EXTRA 300L XTRA ARTEXME 4 Flashes 5 Flashes 6Flashes 7 Flashes e f this error code persists there may a problem with the antenna installation This can be checked with a VSWR meter Check the antenna for opens shorts resistive ground plane connection Low power detected Occurs if output power is below about 33 dBm 2 watts for the 406 signal or 17 dBm 50 mW for the 121 5 MHz output Also may indicate that 406 signal is off frequency For this error code the ELT must be sent back for repair orreplacement Indicates that ELT has not been programmed or is incorrectly programmed Does notindicate erroneous or corrupted programmed data Indicates that the G switch loop between pins 5 and 12 at the D sub connector is not installed ELT will not activate during a crash e Check that the harness D sub jumper is installed by verifying less than 1 ohm of resistance between pins 5 and 12 Indicates that the ELT battery has too much accumulated operation time gt 1hr see below Battery may still power ELT however it must be replaced to meet FAA specifications May also indicate damage to the battery circuit Page Date 31 March 2009 926 7 Section 926 Pilot s Operating Handbook ARTEXME 406 ELT XTRA EXTRA 300L Left blank intentionally 926 8 Page Date 31 March 2009 Handbook XIR A SECTION 927 AIRPLANES REGISTERED IN BRAZIL AND OPERATING UN
192. h place Stay close to the downed aircraft In freezing weather place transmitter inside jacket or coat to keep the battery warm Let the antenna extend outside jacket Keep all moisture and ice away from the antenna connection and the remote connector pins CAUTION Do not turn POINTER portable OFF even by night as search aircraft may be enroute around the clock Even when you have been sighted or think you have the spotting aircraft may not be able to relay an accurate or timely fix on your position without a continued signal Only when the rescue team appears discontinue signalling by using the OFF position Page Date 20 April 2002 904 5 Section 904 Pilot s Operating Handbook Emergency Locator Transmitter X TRA EXTRA 300L 904 4 NORMAL PROCEDURES There is no change of basic normal procedures with the installation of the POINTER 3000 ELT In addition to the existing normal procedures the AUTO position of the unit master switch or the remote switch has to be checked during the preflight check 904 5 PERFORMANCE Not affected 904 6 WEIGHT AND BALANCE Not affected 904 7 DESCRIPTION AND OPERATION OF THE SYSTEM The used Emergency Locator Transmitter is a POINTER 3000 ELT from the POINTER INC Tempe Arizona After an activation the necessity signal is transmitted on the 121 5 MHz and the 243 0 MHz for a period of 48 hours at 20 respectively 2 hours at 50 The inertia sw
193. hapter 4 Normal procedure In addition to this procedures the following points have to be observed A PRIOR TO THE TAKE OFF A release test needs to be conducted to determine safe release operation The test shall be made on both aircraft and glider B TAKE OFF After air tow hook up the tow shall be tighened gently During the following take off and climb the maximum air tow speed of the glider must be observed C CLIMB While climbing the max C H T must be observed Towing light gliders the intial climb angle may be very step Information of the glider pilot is recomended D RELEASE After the release of the glider a gently left handed descent shall be flown to avoid collision of glider and air tow Page Date 16 March 2009 Pilot s Operating Handbook Section 908 EXTRA 300L XTRA Airtow Hook E DESCENT AND LANDING While descending the engine temperatures shall be observed Avoid overcooling Final approach should account for the air tow hanging below the aircraft flight path 908 5 PERFORMANCE The existing POH Data remain valid with the exception of TAKE OFF DISTANCE Conditions Power 2600 Rpm or above and full throttle mixture rich short grass dry and paved level runway no wind takeoff weight of the towing aircraft 820Kg 1808lbs Liftoff speed T O 65 KIAS 120 Km h indicated Obstacle clearance speed over 15m 50ft 70 KIAS 130 Km h indicated For every 5 kts 9 km h headwin
194. he FID button for less than 3 seconds while the unitis in Stanby mode the left side of the bottom line will show the aircraft address NOTE Only an authorized service station is allowed to enter or change the ICAO aircraft address If yu do not have the ICAO aircraft address Please referto your national aviation authority to apply for your aircraft address 912 6 Page Date 15 December 2005 Pilot s Operating Handbook Section 912 EXTRA 300L XTRA FILSER TRT 600 Transponder The Aircraft Identification FID code is displayed on the right bottom line and consists of seven alphanumerical characters CAUTION The ICAO Flight Plan specifies only 7 characters as Flight Identification Filser reserves 8 characters as stated in ED 73B for further expansion of the flight plan The user shall only program 7 characters for FID SELECTING FLIGHT IDENTIFICATION By pressing the button FID for more than 3 seconds the unit will change into the Flight Identification input menu This FID code is a changeable alphanumerical flight number The right lower knob is used to set the cursor position flashing and with the left lower knob the figures A Z blank and 0 9 can be selected To enter the code press the MODE button or the FID button again The FID code is stored in the external aircraft connector a Factory setting for the FID 2222227 b The authorized service station should program a default FID that can be the tail
195. he KT 76A Switching the function selector to the TST position a series of internal tests is performed to check the KT 76 If no faults are detected the reply light illuminates 916 2 LIMITATIONS Not Applicable 916 3 EMERGENCY PROCEDURE IMPORTANT CODES 7500 Use to report a hijacking 7600 Signifies communication failure 7700 Reserved for emergencies 916 4 Page Date 15 December 2005 Pilot s Operating Handbook Section 916 EXTRA 300L XTRA BENDIX KING KT 76A Transponder 916 4 NORMAL PROCEDURE After engine start up turn the function selector to the Standby SBY position Then select the proper reply code by rotating the code select knobs As soon as aircraft is airborne switch the function selector to ON Your KT 76A is now operating ornormal mode To operate in or altitude reporting mode turn the function selector to ALT if aircraft is equipped with altitude encoding equipment 916 4 1 SQUAWK IDENT When you are asked to ident by ATC briefly press the IDENT push button Your aircraft will be positively identified to the Air Traffic Controller 916 5 PERFORMANCE Not Applicable Page Date 15 December 2005 916 5 Section 916 mE Pilot s Operating Handbook BENDIX KING KT 76A Transponder XTRA EXTRA 300L Left blank intentionally 916 6 Page Date 15 December 2005 2 Handbook SECTION 917 BENDIX KING KT 7
196. he adjacent line select key press the right control knob or leave the menu by pressing the MENU button Page Date 31 March 2009 924 11 Section 924 Pilot s Operating Handbook ASPENEFD1000PILOT PFD XTRA EXTRA 300L MENU OPTIONS General Settings Page From the GENERAL SETTINGS page the pilot may Configure the barometric altimeter setting units to inches or millibars in mB ENABLE or DISABLE the display of V Speeds Perform an AHRS RESET V Speed Setting Pages This page is configured by EXTRA according to the speed values given in Section 4 0 1 of this Handbook Values can be changed by the pilot Power Settings Page The POWER SETTINGS is used to monitor and control the source of power to the EFD1000 PILOT PFD including overriding automatic power states From POWER SETTINGS Page the pilot may Switch to Battery Power from External Power Switch to External Power from Battery Power Shut down or Re Start the unit View the External Power Source Voltage View the Internal Battery Status 924 8 HANDLING SERVICING AND MAINTENANCE If the temperature sensor of the RSM is suspected to fail it is advisable to initiate a check of the RSM vent hole Consider that it is necessary to remove the aircraft tail fairing for that purpose Replace the internal battery every 3 years or 2200 hours Check unit and wiring each 100 hours or during annual inspection Referto Aspen Document ZA
197. he aircrew from taking any additional action necessary to deal with the emergency 3 0 2 GENERAL BEHAVIOUR IN EMEREGENCY SITUATIONS As soon as one of the crew member becomes aware that an emergency situation exists he must immediately alert the other crew member of the situation In any emergency situation contact should be established with a ground station as soon as possible after completing the initial corrective action Include position altitude heading speed nature of the emergency and pilot s intentions in the first transmission There after the ground station should be kept informed of the progress of the flight and of any changes or developments in the emergency Three basic rules apply to most emergencies and should be observed by each aircrew member 1 Maintain aircraft control 2 Analyze the situation and take proper action 3 Land as soon as possible as soon as practical The meaning of as soon as possible and as soon as practical as used in this section is as follows Land AS SOON AS POSSIBLE ASAP Emergency conditions are urgent and require an immediate landing at the nearest suitable airfield considering also other factors such as weather conditions and aircraft mass Land AS SOON AS PRACTICAL Emergency conditions are less urgent and in the aircrews judgement the flight may be safely continued to an airfield where more adequate facilities are available WARNING Make only one attempt to restore an a
198. he case of unknown filling the smoke oil tanks should be drained and refilled with a known quantity If this is not possible the most adverse case has to be taken for calculation This may be either completely full or completely empty tanks 909 7 DESCRIPTION OF THE SYSTEM On pilot s demand the smoke system produces a trail of smoke by injection of smoke oil straight paraffin oil into the engine exhaust The smoke oil is vaporised by the exhaust gas heat and is visible as dense smoke after leaving the exhaust For smoke system activation the SMOKE ARM switch located on the pilot instrument panel needs to be switched ON first The smoke ON OFF toggle switch is located on top of the Page Date 20 September 2006 909 5 Section 909 Pilot s Operating Handbook Smoke System XTRA EXTRA 300L throttle lever For filling the smoke oil tanks the SMOKE REFILL switch needs to be ON After the refill process is completed the SMOKE REFILL has to switched OFF When both switches SMOKE ARM and SMOKE REFILL are in the ON position the smoke system is not energized and will not run There are two different systems approved A DUAL PUMP SYSTEM The main smoke oil tank is filled by a refill pump through a quick connector located in the aircraft belly fairing The separate floptube smoke oil tank is interconnected to the main smoke oil tank and gravity fed Filled tanks are detected by afloat switch pl
199. he following placards replace the existing placards when the aircraft is delivered in configuration 2 FUEL SELECTOR VALVE in both cockpits near selector valve handle WING TANKS usable 120 L 31 7 US GAL usable 67 L 17 7 US GAL CENTER f AC 921 4 Page Date 8 October 2009 Pilot s Operating Handbook Section 921 EXTRA 300L Lycoming AEIO 580 B1A Engine CENTER TANK INDICATION On the rear instrument panel SHOWS ZERO IN LEVEL FLIGHT next to the fuel quantity indicator BELOW 9 L 2 4 US GAL UNUSABLE FUEL 2 L 0 5 US GAL 921 2 5 Instrument Markings CYLINDERHEAD TEMPERATURE INDICATOR yellow arc lt 150 F green arc 150 F 435 yellow arc 435 F 465 F redline 465 F MANIFOLD PRESSURE INDICATOR green arc 10 Hg 30 Hg 921 2 6 Noise Level The noise level with silencer Gomolzig EA300 606000 1 and propeller MTV 9 B C C 198 25 at 2600 RPM has been established in accordance with ICAO Annex 16 as 77 8 dB A In addition The noise level with silencer Gomolzig EA300 606000 6 in 1 and propeller MTV 9 B C C 198 25 at 2600 RPM has been established in accordance with FAR 36 Appendix G incl Amdt 36 28 as 77 5 dB A No determination has been made by the Federal Aviation Administration that the noise level of this aircraft is or should be acceptable or unacceptable for operation at into or out of any airport 92
200. he smoke oil tanks for proper attachment Clean the overpressure check valve if required remove oil residue Clean the injector nozzle if required remove carbon debris Clean the filter element After each flight with activated Smoke System Clean the aircraft belly fairing and the rudder cable from smoke oil contamination NOTE The rudder cables might suffer from increased wear when they are covered with smoke oil and dust Page Date 20 September 2006 909 7 Section 909 junii Pilot s Operating Handbook Smoke System XTRA EXTRA 300L Left blank intentionally 909 8 Page Date 20 September 2006 2 Handbook XTR A SECTION 910 ACRO Ill CATEGORY Table of Contents Paragraph Page 910 1 GENERA e 910 3 910 2 LIMITATIONS e 910 3 910 3 EMERGENCY PROCEDURES caa ied aane 220 Ce dama aided ua 910 4 910 4 NORMAL PROCEDURES 910 4 910 5 PERFORMANCE a 910 5 910 6 WEIGHT AND BALANCE 2 u 910 6 910 7 DESCRIPTION AND OPERATION OF AIRCRAFT AND ITS SYSTEMS 910 8 910 8 HANDLING SERVICING AND MAINTENANCE 910 8 Page Date 20 April
201. iables Sufficiently detailed information are provided in the tables so that conservative values can be selected and used to determine the particular performance figure with reasonable accuracy All speeds in this chapter are Indicated Air Speeds IAS except otherwise stated The performance figures below are given underfollowing conditions 1 Maximum allowed weight 950 kg 2095 Ibs except otherwise stated 2 Take off and landing on concrete surface 3 No wind 4 Standard atmospheric condition 5 1 2 Definitions of Terms For definition of terms abbreviations and symbols refer to section 1 General 5 1 3 Sample Problem TAKE OFF CONDITIONS Field Pressure Alt 2000 ft 610 m Temperature 15 C 59 F Wind Component Headwind 8KT 15 km h Field Length 3000 ft 914 m CRUISE CONDITIONS Total Distance 400 NM 741 km Pressure Altitude 8000 ft 2438 m Temperature ISA 1 C 30 F Page Date 16 March 2009 5 3 Section 5 Pilot s Operating Handbook Performance XTRA EXTRA 300L TAKE OFF Take Off Distance is shown by Fig 5 5 Example T O Weight 870 kg 1918 Ibs Ground Roll 112 m 367 ft Total Distance to clear a 50 ft obstacle 248 m 813 ft These distances are well within the available field length incl the 8 kts 15 km h headwind RATE OF CLIMB Fig 5 6 shows the Rate Of Climb using Take off Power The Rate of Climb at 2000 ft 610 m 2320 ft min 11 8 m s The Time to Climb f
202. ic activation by the G switch 904 8 HANDLING SERVICING AND MAINTENANCE Visually inspect the unit at regular intervals for cleanliness and secureness Check whip antenna mounting and cable connections for tightness In accordance with FAA regulations batteries must be replaced after 2 years shelf or service life or for any of the following reasons after the transmitter has been used in emergency situation including any inadvertent activation of unknown duration after the transmitter has been operated fore more than one cumulative hour on or before battery replacement date Page Date 20 April 2002 904 7 Section 904 mE Pilot s Operating Handbook Emergency Locator Transmitter EXTRA 300L Left blank intentionally 904 8 Page Date 20 April 2002 2 Handbook XTR A SECTION 905 EXTERNAL POWER Table of Contents Paragraph Page 905 1 GENERAL MM 905 3 905 2 LIMITATIONS 905 3 905 3 EMERGENCY PROCEDURES nana Da o Ce dama 905 3 905 4 NORMAL PROCEDURES III UU 905 3 905 5 PERFORMANCE c 905 4 905 6 WEIGHT AND BALANCE 2 1 u asas nasus anas asas as ann 905 4 905 7 DESCRIPTION OF THE SYSTEM imt ain eaa nm
203. ion the ID code is displayed in the right window the ident window A fault in the altitude interface or an invalid altitude input to the KT 73 will cause the display to show a series of dashes when the ALT mode is selected SBY SBY is displayed in the altitude window when SBY mode is selected by the Function Selector Knob In addition the ID code is displayed in the right window the ident window GND GND is only displayed on the left side altitude window when the aircraft is on ground The ID code is shown on the right side the ident window FLT IDT The FLT IDT is annunciated and the flight ID is illuminated in the display area when the FLT ID mode is selected by the Function Selector Knob TEST TEST is displayed in the Test mode if no faults are detected SBY FXYZ If one or more fault is detected the Test mode SBY is displayed in the altitude window and the ident window will cycle through all detected faults indicated by FXYZ The XYZ denotes the specific fault 917 1 5 PROGRAMMING MODE The programming mode is normally set at of installation including the unique Mode S aircraft address The programming mode should not be used during flight Refer to the KT 73 Installation Manual 006 10563 0004 latest revision 917 1 6 AIR GROUND SWITCHING The AUTO GND Automatic Ground Programming function is not available 917 6 Page Date 31 March 2009 Pilot s Operating Handbook E S
204. isted in the following list NOTE If acrobatic maneuvers will be performed with co pilot or passenger the pilot has to check and attend the physiological capability before and during acrobatic maneuvers due to the high possible g loads Check weight and C G 2 6 Page Date 20 April 2002 Pilot s Operating Handbook Section 2 EXTRA 300L lt s XTRA Limitations Maneuvers Recommended entry speeds IAS Symbol Remarks min knots km h max knots km h Segment horizontal Line Vs e 45 climbing 80 148 90 up VNE 1 45 diving Vs VNE a reduce throttle 90 diving Vs VNE 1 reduce throttle 1 4 Loop climb 100 185 190 352 m Looping 100 185 190 352 ner Stall turn 100 185 190 352 t Aileron roll 80 148 VA gt full deflection Snap roll 80 148 140 259 z tail slide 100 185 190 352 Spin Vs Inverted spin Vs Knife edge 2150 278 105 Inverted Flight 190 352 ERE 4 min CAUTION Particular caution must be exercised when performing maneuvers at speeds above 158 KIAS 293 km h Large or abrupt control inputs above this speed may impose unacceptably high loads which exceed the structural capability of the aircraft NOTE For Acrobatic Maneuvers see Section 4 All maneuvers can be performed in upright and inverted flight attitude 2 9 LOAD FACTOR 2 9 1 NORMAL F
205. itch releases the necessity signal after a G force of 5 2 0 g in aircraft longitudinal axis and a duration of 11 5 0 milliseconds When properly installed parallel to the line of flight the ELT will not activate due to turbu lence normal operation or aerobatics POINTER PORTABLE ELT MAYOR SYSTEM COMPONENTS The POINTER PORTABLE ELT System consists of the following components Telescopic Whip Antenna Antenna Remote Connector bracket Remote switch ELT mounting optional bracket 904 6 Page Date 20 April 2002 Pilot s Operating Handbook Section 904 EXTRA 300L X TRA Emergency Locator Transmitter OPERATING INSTRUCTION OF THE TRANSMITTER The operation of the ELT is possible over the master unit switch or over the remote switch optional in the panel UNIT MASTER SWITCH ON used to activate the transmitter for test or emergency situations used to de activate transmitter or to insure non activation by 2 handling z AUTO used to arm the Pointer Portable for automatic activation by the G switch only REMOTE SWITCH optional ON used to remotely activate the transmitter for test or emergency situation An example of such an emergency situation would be forced landing with an impact insufficient to activate the Rolamite G switch AUTO used to arm the Pointer Portable for automatic activation by the switch only OFF used to de activate transmitter after automat
206. ius about the transmitter Due to the better signal integrity ofthe 406 MHz its location accuracy is within abouta 3 km radius 926 2 LIMITATIONS The operation limitations are not effected due to the installation ofthe ARTEX ME 406 ELT Forthe location and operation of the transmitter the following placards have to be attached to the aircraft ELT LOCATED HERE outside on the left fuselage in the vicinity of the ELT unit above the ELT circuit breaker circuit breaker and placard installed up to SN 1320 only next to the ELT remote switch as close to the ELT remote switch as practical Page Date 19 April 2012 926 3 Section 926 Pilot s Operating Handbook ARTEXME 406 ELT XTRA EXTRA 300L 926 3 EMERGENCY PROCEDURES ncase of aforced landing turn the remote switch in the rear panel to the ON position prior to touch down Although the ELT will be activated automatically after an aircraft accident or forced landing with high G force turn additionally the remote switch in the rear panel to the ON position After sighting rescue aircraft Switch the remote switch to the ARM position to prevent radio interference Attempt contact with rescue aircraft with the radio transceiver set to a frequency of 121 5 MHz If no contact is established switch the remote switch to the ON position immediately If the function of the remote switch is in doubt
207. ive keys are also used when navigating the main menu 924 7 3 POWER CONTROL To enhance safety the EFD1000 PILOT PFD includes an internal battery that allows the system to continue to operate in the event of a failure of the aircraft electrical system This ensures that the EFD1000 PILOT PFD flightinstrumentcontinues to remain available for a period of time following the loss of all external supply power This internal battery is not required by regulation however it is good practice to verify the status of the battery prior to takeoff The EFD1000 PILOT PFD receives aircraft power from the battery bus via the PFD circuit breaker Whenever indicated airspeed is invalid or below 30 KIAS the EFD1000 PILOT PFD will power up and power down with the application or removal of external power To turn on the system turn on the AVIONIC switch when Battery Master is ON Turning off the system is vice versa A message is presented during the normal power down sequence to enable the pilot to abort the shutdown and switch to internal battery The AHRS will perform an internal test during EFD1000 PILOT PFD power up The aircraft should remain stationary during the AHRS power up and alignment sequence Ifthe aircraftis moved during AHRS alignment it will take longer for accurate attitude and heading information to be presented to the pilot Attitude and heading information is presented once the AHRS completes the alignment process When IAS is greater than 30
208. kg x cm L Ib x in US gal 157 865 459 553 648 742 836 931 1026 1120 1215 1291 WINGTANK kg x cm Ib x in 72 15 9 360 313 144 31 8 721 629 28 8 63 5 1442 1257 43 2 95 3 2164 1886 57 6 127 0 2885 2514 72 0 158 8 3607 3144 86 4 190 5 4328 3771 Page Date 5 December 2008 922 7 Section 922 Pilot s Operating Handbook Center Tank Increased Capacity X TRA EXTRA 300L 922 7 DESCRIPTION OF THESYSTEM Refer to Figure 922 1 The center fuel tank 5 with increased fuel capacity is installed in the same place and in the same manner as the standard fuel center tank This includes the vent line 2 and the fuel filler 3 location However the tank is increased in down and rearward direction The steel tubes of the fuselage carrying the tank and the tank mounting are reinforced The fuel contents probe 4 has been changed while the indicator is still the same The total fuel capacity of the center tank is 60 L 15 9 US gal The total fuel capacity of the acro tank 1 is 9 L 2 4 US gal The usable fuel quantity of both center and acro tank is 67 L 17 7 US gal Y Figure 922 1 Center Tank and Environment 922 8 HANDLING SERVICING AND MAINTENANCE Notaffected 922 8 Page Date 5 December 2008 2 Handbook SECTION 923 GARMIN GTX328 TRANSPONDER Table of Contents
209. le to minimize antenna shielding by locating the antenna where dead spots are only noticed during abnormal flight attitudes CAUTION The KT 73 should be turned off before starting or shutting down aircraft engine The KT 73 Transponder is powered on by rotating the Function Selector Knob from the OFF position to any functional mode position Page Date 31 March 2009 917 3 Section 917 Pilot s Operating Handbook BENDIX KING KT 73 Transponder XTRA EXTRA 300L 917 1 1 FUNCTIONSELECTOR KNOB The following operating modes can be chosen by the Function Selector Knob OFF Powers off the KT 73 When the unit is turned to another mode it will reply or squitter within two seconds according to the selected mode FLT ID Selects the Flight ID mode displaying the 8 character Flight ID or registration marking of the airplane When in Flight ID mode the transponder will not reply to any interrogations SBY Selects the Standby mode displaying the last active identification code When in Standby mode the transponder is energized but will not reply to any interrogations TST Selects the Test mode displaying all display segments for a minimum of 4 seconds A series of internal tests is performed to check its integrity verify all aircraft specific configuration data and make hardware and squitter checks When in Flight TST mode the transponder will not reply to any interrogations In addition the display brightness can be man
210. ly 928 2 Page Date 17 January 2013 Pilot s Operating Handbook Section 928 EXTRA 300L XTRA Landing Light 928 LANDING LIGHT 928 1 GENERAL To improve the visibility of the aircraft during approach and landing a landing light can be integrated in the RH lower cowling 928 2 LIMITATION Nochange 928 5 EMERGENCY PROCEDURES Nochange 928 4 NORMALPROCEDURES Nochange 928 5 PERFORMANCE Nochange 928 6 WEIGHT AND BALANCE Refer to the Equipment List in section 6 of this Handbook 928 7 DESCRIPTION OF THE SYSTEM The landing light is controlled by the LANDING LIGHT switch on the right instrument panel The system is protected by the LANDING LIGHT circuit breaker o 9 9 N 9 o 9 9 9 OFF LANDING LIGHT 8882992990909 j 10 ooooooooooooo O LIGHT C C t j Page Date 17 January 2013 928 3 Section 928 Pilot s Operating Handbook Landing Light XTRA EXTRA 300L 928 8 HANDLING SERVICING AND MAINTENANCE Nochange 928 4 Page Date 17 January 2013
211. ly to Warnings Cautions and Notes WARNING gt Operating procedures techniques etc which could result in personal injury or loss of life if not carefully followed CAUTION gt Operating procedures techniques etc which could result in damage to equipment if not carefully followed NOTE gt An operating procedures technique etc which is considered essential to emphasize Shall Will Should and May The words Shall or will shall be used to express a mandatory requirement The word should shall be used to express nonmandatory provisions The word may shall be used to express permissible Page Date 31 March 2009 XTRA Pilot s Operating Handbook EXTRA 300L MAIN TABLE OF CONTENTS Section 1 GENERAL 2 LIMITATIONS 3 EMERGENCY PROCEDURES 4 NORMAL PROCEDURES 5 PERFORMANCE 6 WEIGHT amp BALANCE EQUIPMENT LIST 7 AIRPLANE amp SYSTEMS DESCRIPTIONS 8 AIRPLANE HANDLING SERVICE amp MAINTENANCE 9 SUPPLEMENTS Page 2 1 3 1 5 1 6 1 8 1 9 1 vi Page Date 31 March 2009 Pilot s Operating Handbook XTRA EXTRA 300L Paragraph 1 0 1 1 1 2 1 3 1 3 1 1 3 2 1 3 3 1 3 4 1 3 5 1 3 6 1 3 7 1 4 1 5 1 5 1 1 6 1 7 1 8 SECTION 1 GENERAL Table of Contents Page DESGRIPTION gm EE 1 3 SPECIFICATION OF GLASS UL LULU uu 1 3 MANUFACTURER pe
212. maller area The direct to key provides access to the direct to function which allows you to enter a destination waypoint and establishes a direct course to the selected destination The MENU key displays a context sensitive list of options This options list allows you to access additional features or make settings changes which relate to the currently displayed page The clear key CLR is used to erase information or cancel an entry Press and hold this key to immediately display the Default Navigation Page regardless of which page is currently displayed The enter key ENT is used to approve an operation or complete data entry Itis also used to confirm information such as during power on The large right knob used to select between the various page groups NAV WPT AUXorNRST With the on screen cursor enabled the large right knob allows you to move the cursor about the page 925 6 Page Date 31 March 2009 Pilot s Operating Handbook Section 925 EXTRA 300L XTRA GARMIN GNC 420W The small right knob CRSR is used to select between the various pages within one ofthe groups listed above Press this knob momentarily to display the on screen cursor The cursor allows you to enter data and or make a selection from a list of options BOTTOM ROW KEYS The nearest NRST key displays the nearest airports page Then turning the small right knob steps through the NRST pages The OBS key is used to select ma
213. mandatory Foreign operating rules and any references to such rules in the basic manual and approved supplements are not applicable in Brazil The aircraft must be equipped and operated in accordance with Brazilian operating requirements NOTE A Kinds of Operation Equipment List may not necessarily apply in Brazil Page Date 31 October 2013 927 3 Section 927 Pilot s Operating Handbook AIRPLANES REGISTERED IN BRAZIL XTRA EXTRA 300L 927 2 LIMITATIONS 927 2 1 ENGINE Thefollowing Textron Lycoming engines are certified 1 Engine type AEIO 540 L 185 with rated maximum 300HP 2700RPM 2 Engine type AEIO 580 B1A with rated maximum 315HP 22700RPM 927 2 2 KINDS OF OPERATIONAL LIMITS Operation is limited to VFR day Use of GPS is prohibited as primary means for navigation Optional GPS is approved as supplemental means for navigation only Wide Area Augmentation System WAAS functionality Since the WAAS is not available in Brazil any kind of Global Navigation Satellite System GNSS approaches is prohibited even though optional GPS System installed e g GARMIN GNC420W may be capable of receiving WAAS 927 2 3 OPERATINGPLACARDS The following placard has to be attached to the aircraft replacing the related placard in English language COMBUSTIVEL adjacent to both wing fuel tank filler caps and AVGAS 100 100LL fuselage center fuel tank filler cap 927 3 EMERGENCY PROCEDURES Not affected 927 4 NO
214. me airspaces Mode S Elementary Surveillance functionality is required Page Date 15 December 2005 2 13 Section 2 Pilot s Limitations NORMAL ACROBATIC 1 seat 2 seats ENGINE CONTROL 1 RPM indicator 1 1 1 2 Exhaust gas temperature ind 0 0 0 3 Cylinder head temperature ind 0 0 0 OIL 1 Oil temperature indicator 1 1 1 2 Oil pressure indicator 1 1 1 FLIGHT CREW EQUIPMENT 1 Parachute rear 0 j i 2 Parachute front 0 0 3 Seat belt rear 1 1 1 4 Seat belt front 1 0 1 5 Headset rear 1 1 1 6 Headset front 1 0 1 NOTE The zeros 0 used in the above list mean that either the equipment or system or both were not required for type certification for that kind of operation Either equipment or systems in addition to those listed above may be required by the national operating regulations The asterisks used in the above list mean that latest national aviation regulations must be observed in determining whether the equipment and or system are required According FAR Part 91 General Operating and Flight Rules each occupant of an US registered airplane must wear an approved parachute when performing acrobatic maneuvers Extra Flugzeugproduktions und Vertriebs GmbH considers acrobatics without wearing an approved parachute to be unsafe 2 16 NOISELEVEL The noise level with silencer Gomolzig 606000 6 in 1 and propeller MTV 14 B C C190 17 has been established in a
215. med The Table of Contents shows all EXTRA Supplements available for the EXTRA 300 L A check mark in the Section column indicates that the corresponding supplement must be included in this POH Page Date 31 March 2009 9 3 Section 9 Pilot s Operating Handbook Supplements XTRA EXTRA 300L Left blank intentionally 9 4 Page Date 20 April 2002 2 Handbook XTR A SECTION 901 STEERABLE TAIL WHEEL Table of Contents Paragraph Page 901 1 901 3 901 2 LIMITATION ee 901 3 901 3 EMERGENCY PROCEDURES u IIIa iod nana 220 901 3 901 4 NORMAL PROCEDURES 901 3 901 5 PERFORMANCE uuu u u as usu usa uuu 901 3 901 6 WEIGHT AND BALANCE uuu u 901 3 901 7 DESCRIPTION OF THE SYSTEM III ne open it aaaeaii daie 901 3 901 8 HANDLING SERVICING AND MAINTENANCE mannna 901 4 Page Date 20 April 2002 901 1 Section 901 Pilot s Operating Handbook Steerable Tail Wheel XTRA EXTRA 300L Left blank intentionally 901 2 Page Date 20 April 2002 Pilot s Operating Handbook Section 901 EXTRA 300L XTRA Steerable Tail Wheel 901 901 1 901 2 901 3 901 4 901 5 9
216. mory stores the times and dates when new Absolute Extreme Values occur They are shown if you push S2 next In this case during the next twelve seconds the LC Display shows under the title MAX DATE the time and date of the positi ve Absolute Extreme Value and under the title the time and date of the negative Absolute Extreme Value Afterwards the instrument returns into the Normal Operating Mode If you push S1 instead of S2 the LC Display will show the current time and date If there is no button pushed for about five seconds the instrument will return into the Normal Operating Mode 6 OUTPUT OF TIME AND DATE push button four times S1 The LC Display will exhibit time and date after you have pushed S1 for four times For example 02 52 PM 12 09 93 is the ninth December 1993 at 2 o clock and 52 minutes in the afternoon If you want to set the clock you have to push 51 for another time otherwise the instrument returns into the Normal Operating Mode 7 SETTING OF THE CLOCK push button five times S1 You can only set the clock if you know the right four digit code If you push 51 for five times the LC Display shows a request to enter the code You can change the code digit by pushing S2 To confirm your input of a digit you have to push S1 If the entered code digits are wrong or you wait longer than six seconds the instrument will return into the Normal Operating Mode CODE 0
217. n G wit hin seconds to store the code under the corresponding button d If neither button G is pressed within seconds the flashing stops and the storage operation is aborted NOTE If one of the two buttons F or G is pressed without the STO button having been pressed beforehand then the stored code allocated this button appears in the code display and is switchedto active after 3 seconds can be changed inthe configuration mode If the same button is again pressed within 3 seconds the previous code appears 2 Activation of the VFR codes a Pressthe VFR push button 1 or 2 F G The selected code is then displayed After 3 seconds the displayed code becomes activate and overwrites the previously set reply code b Pressing button F or G again within 3 seconds reactivates the previously set reply code NOTE When the unit is delivered the store buttons are not assigned a code This means that if these buttons are pressed for 0 5 seconds is shown in the code display and the transponder then switches back to the previously active code IMPORTANT CODES 1200 The VFR code for any altitude in the US Refer to ICAO standards elsewhere 7000 The VFR code commonly used in Europe Refer to ICAO standards 0021 The VFR code commonly used in Germany default is set to 0021 at time of installation 7500 Hijack code Aircraft is subject to unlawful interference 7600 Loss of communications 7700 Emergenc
218. n be flown with the elevator trim In this case trim nose up to the desired speed and control horizontal flight or descend with engine power For landing trim nose up and establish a shallow descend by adjusting throttle To flair the plane gently increase power to bring the nose up to landing attitude 3 8 Page Date 31 March 2009 Pilot s Operating Handbook XTR A EXTRA 300L SECTION 4 NORMAL PROCEDURES Table of Contents Paragraph Page 4 0 ilz lzini 4 3 4 0 1 Airspeeds for Normal 4 3 4 0 2 Checklist and 4 3 4 1 PHEFLEIGHTINSPEGCTION une eui ure ene ends 4 4 4 1 1 Exterior Inspection IIustratiOri 4 4 4 1 2 Gerierd 4 4 4 2 CHECKLIST PROCEDURES 1 once 4 4 4 3 STARTING PROCEDURES 5 5 2 21 u 4 6 4 3 1 66 it ette Dee 4 6 4 3 2 POU ENGIN r u 4 6 4 4 TAXIING THE AIRCRAEFT 4 6 4 5 TAKE OFF PROCEDURE L iioii eere 4 7 4 5 1 Before Em 4 7 4 5 2 Ir crop c mH 4 7 4 6 CLIMB M 4 7 4 7 CRU
219. n external altitude source which is not adjusted for barometric pressure Any time the function ON or ALT is selected the transponder becomes an active part of the Air Traffic Control Radar Beacon System ATCRBS The transponder also responds to interrogations from TCAS equipped aircraft 923 1 2 CODESELECTION Code selection is done with eight keys 0 7 providing 4 096 active identification codes Pushing one of these keys begins the code selection sequence Digits that are not yet entered appear as dashes The new code is activated when the fourth digit is entered Pressing the CLR Key moves the cursor back to the previous digit Pressing the CLR Key when the cursor is on the first digit of the code or pressing the CRSR Key during code entry removes the cursor and cancels data entry restoring the previous code Press the CLR Key up to five seconds after code entry is complete to return the cursor to the fourth digit The numbers 8 and 9 are not used for code entry only for entering a Count Down time and contrast and display brightness IMPORTANT CODES 1200 The VFR code for any altitude in the US Refer to ICAO standards elsewhere 7000 The VFR code commonly used in Europe Refer to ICAO standards 7500 Hijack code Aircraft is subject to unlawful interference 7600 Loss of communications 7700 Emergency 7777 Military interceptor operations Never squawk this code 0000 Military use Not enterable 923 4 Page Date 5 De
220. n limitations has to be reported by the pilot so that necessary inspection or maintenance procedures according to the SERVICE MANUAL EA 300 L can be performed 2 2 AIR SPEED IAS Never Exceed Speed Vue 220 407 km h Max Structural Cruising Speed Normal Cat Vno 140 259km h Max Structural Cruising Speed Acro Acro Vno 158knots 293km h Maneuver Speed Normal Cat Va 140 259km h Maneuver Speed Acro Acro 11 V 158knots 293km h 2 3 CROSS WIND COMPONENT Max demonstrated cross wind component for take off and landing is 15 knots 27 km h 2 4 ENGINE Engine type Textron Lycoming AEIO 540 L 185 AEIO 540 L1B5D with rated maximum 300 2700 RPM Page Date 31 March 2009 2 3 Section 2 Pilot s Operating Handbook Limitations XTRA EXTRA 300L 2 4 1 FUEL Minimum grade aviation gasoline 100 100LL for alternate fuelgrades see latest revision of Lyc 5 1 No 1070 Total fuel capacity 171 L 45 1 US gal Usable fuel capacity 165 5 L 43 6 US gal For acrobatic flight wing tanks must be empty Total fuel capacity for acrobatic 51 L 13 4 US gal in acro amp center tank Usable fuel capacity for acrobatic 45 5 L 12 0 US gal in acro amp center tank 2 4 2 ENGINE LIMITATIONS a Rotational Speed Maximum Take Off and Maximum Continuous 2700 rpm b Oil temperature Max 118 245 F c Oil capacity Maximum sump capacity 16 US qt Minimum sump cap
221. ndicator UNUSABLE FUEL 2 L 0 5 US GAL 922 3 EMERGENCY PROCEDURES Not affected 9224 NORMAL PROCEDURES Not affected Page Date 5 December 2008 922 3 Section 922 Pilot s Operating Handbook Center Tank Increased Capacity X TRA EXTRA 300L 922 5 PERFORMANCE 922 5 1 Cruise Performance Range and Endurance values for a T O Weight of 950 kg 2095 Ib including fuel for warm up and Take Off from SL max cont Power climb to cruising altitude and a reserve of 21 L 5 55 gal for 45 minutes with 45 Power 2 L 0 53 gal unusable fuel is taken into account At ISA Conditions PA Eng Manif Power Setting Fuel TAS IAS Endur Range Mixture Press Consumption ft m rpm inHg hp L h gal h kts km h kts km h h nm km Best 2000 2700 274 95 286 882 23 3 182 6 338 173 320 1 73 317 587 Power 610 2400 25 1 75 225 68 7 18 2 167 6 310 160 296 2 22 372 689 Power 2200 242 65 195 50 5 13 3 159 3 295 152 282 3 03 481 891 Economy 2000 23 5 55 165 426 11 3 150 2 278 144 267 3 58 538 996 Economy 2000 202 45 185 36 5 9 6 139 9 259 134 248 418 584 1082 Economy 4000 2700 25 4 89 267 82 7 181 5 168 1 85 333 Power 1219 2400 24 6 75 225 687 1 8 336 311 617 8 2 170 9 317 158 293 222 377 698 Power 3 3 162 4 301
222. nes ON OFF After having switched on the AVIONIC MASTER switch the TRT 800 hasto be turned on by hand by pressing the ON OFF button forless then 1 second The display will first show the transponder type and the software and firmware version To turn off the unit the button ON OFF must be pressed for more then two seconds or the AVIONIC MASTER switch must be placed to the OFF position ACS is the default operation mode and the transponder replies to Mode A C and S interrogations The pressure altitude will be displayed as Flight Level SQUAWK SELECTION Squawk selection is done with the four rotating knobs to provide 4096 identification codes The assignments of the knobs starting at top left are X selection of thousands 0 7 X selection of hundreds 0 7 X selection of ten 0 7 X selection of one 0 7 The code is entered in the lower line and remains inactive By pushing the UP AND DOWN ARROWS button the squawk code is transferred to the upper line and becomes active The code in the upper line is always the active one IMPORTANT CODES 1200 The VFR code for any altitude in the US Refer to ICAO standards elsewhere 7000 The VFR code commonly used in Europe Refer to ICAO standards 0021 The VFR code commonly used in Germany default is set to 0021 at time of installation 7500 Hijack code Aircraft is subject to unlawful interference 7600 Loss of communications Page Date 15 December 2005 913 5 Se
223. ng Tank Capacity For the adjustment Best Economy simply lean the mixture to achieve the top exhausttemperature peak EGT Leaning without exhaust gas temperature EGT gage and flowmeter Slowly move mixture control from Full rich position towards lean position Continue leaning until slight loss of power is noted Loss of power may or may not be accompanied by rough engine run Then enrich until engine runs smoothly and power is regained CAUTION Always return the mixture to full rich before increasing power settings 907 6 WEIGHT AND BALANCE LOADING WEIGHTS AND MOMENTS TOTAL FUEL CAPACITY 205 Litre 54 1 US GAL ACRO amp CENTER TANK WING TANK Litre KG KG x CM Litre KG KG x CM US GAL LBS LBS x IN US GAL LBS IN x LBS 65 143 10 26 72 159 360 313 144 318 20 53 144 31 8 721 629 18 0 39 7 40 10 6 28 8 63 5 1442 1257 21 6 476 60 15 9 432 953 1886 55 6 80 21 1 57 6 127 0 2514 63 5 100 26 4 72 0 158 8 3144 71 4 120 31 7 86 4 190 5 3771 80 9 140 36 9 100 8 222 3 4402 154 40 7 110 9 244 6 4842 Page Date 16 March 2009 907 5 Section 907 Pilot s Operating Handbook Long Range Wing Tank Capacity XTRA EXTRA 907 7 DESCRIPTION OF THESYSTEM Wing tank The leading edge section of each wing in front of main spars forms an integral fuel tank providing two int
224. ng conditions may necessitate some variation from these procedures Perform Pre flight inspection Set propeller governor control to High RPM position Open throttle approximately 1 4 travel 1 2 3 4 Master switch OFF 5 Put the external power plug into the board receptacle 6 Turn boost pump ON 7 Move mixture controlto FULL RICH until a slight but steady fuel flow is noted approximately 3 to 5 seconds and return mixture control to IDLE CUT OFF Turn boost pump OFF CAUTION Pay attention to objects and persons in the propeller operating area Hold the canopy tight 8 Apply the brakes 9 Engage starter 10 When engine fires release the ignition switch back to BOTH 11 Pull the external power plug from the board receptacle 12 Move mixture control slowly and smoothly to FULL RICH Page Date 15 December 2005 905 3 Section 905 Pilot s Operating Handbook External Power EXTRA 3001 13 Check the oil pressure gauge If minimum oil pressure is not indicated within 30 seconds shut off the engine and determine trouble 14 Master switch ON 905 5 PERFORMANCE Not affected 905 6 WEIGHT AND BALANCE Not affected 905 7 DESCRIPTION OF THE SYSTEM The external power receptacle is attached left under the rear seat The main relais is located at the left side of the firewall above the starter relais For the avoidance of sparks this relais does
225. ng digit If no cursor is visible the first digit flashes after a clockwise rotation and the last digit after a counter clockwise rotation When the code is being changed in the ON or ALT position the transponder temporarily switches to the standby mode The active time of the cursor and the rate of flashing can be changed in the configuration mode If the cursor is not moved again within of 3 seconds can be changed in configuration mode or if the cursor is moved so far that it can no longer be seen in the display field or the identification Switch is pressed in the ON or ALT mode the code currently set is switched active NOTES Whilst settings are taking place the transmission branch of the transponder is inhibited to prevent unintentional transmission If only two digits were named by e g Squawk alpha 64 then a zero is to be used for positions three and four i e 6400 The last used code is stored in each case andis also activated when the transponder is switched on SPECIAL VFR CODINGS 1 Two user specific VFR codes can be stored and activated on the transponder Storing a new VFR code a Setthe code to be stored in accordance with section B Page Date 15 December 2005 919 5 Section 919 Pilot s Operating Handbook BECKER ATC 4401 Transponder XTRA EXTRA 300L b Press store push button STO J the set code then flashes c Pressthe VFR1 push button F or the push butto
226. not switch before a safe contact from plug to recepta cle will be ensured During the engine start the master switch has to be switched in OFF position for the disconnection of the battery from the aircraft electric circuit lt lt N N N N N N N N N External Power Relais Diode By 550 100 2 2 External Power Receptacle AN 2552 3A 12V 28AH Main Relais was BATTERY T T Master Switch Starter Relais STARTER 905 4 Page Date 15 December 2005 Pilot s Operating Handbook Section 905 EXTRA 300L XTRA External Power 905 8 HANDLING SERVICING AND MAINTENANCE Not affected Page Date 20 April 2002 905 5 Section 905 junii Pilot s Operating Handbook External Power XTRA EXTRA 300L Left blank intentionally 905 6 Page Date 20 April 2002 555 2119 Handbook SECTION 906 DIGITAL RPMINDICATOR Table of Contents Paragraph Page 906 1 GENERALE ne u dee 906 3 906 2 LIMITATIONS cn 906 3 906 3 EMERGENCY 44444 400 906 3 906 4 NORMAL PROCEDURES ere eor cna c e Gu Y 906 3 906 5 906 4 906 6 WEIGHT AND BALANCE
227. nual or automatic sequencing of waypoints Pressing the OBS key selects OBS mode which will retain the current active to waypoint as your navigation reference even after passing the waypoint i e prevents sequencing to the nextwaypoint Pressing the OBS key again will return to normal operation with automatic sequencing of waypoints Whenever OBS mode is selected you may set the desired course to from a waypoint using the OBS Page or an external OBS selector on your HSI or CDI The message key MSG is used to view system messages and important warnings and requirements The flight plan key FPL allows you to create edit activate and invert flight plans as well as access approaches departures and arrivals A closest pointto flight plan feature is also available from the flight plan key NOTE Whenever the GNC 420W is displaying a list of information that is too long for the display screen ascrollbar will appear along the right hand side of the display The scroll bar graphically indicates the number of additional items available within the selected category Simply press the small right knob to activate the cursor and turn the large right knob to scroll through the list The procedures key PROC allows youto select and remove approaches departures and arrivals from yourflightplan When using aflight plan available procedures for your departure and or arrival airport are offered automatically Otherwise you may selectthe desire
228. ode IMPORTANT CODES 1200 The VFR code for any altitude in the US Refer to ICAO standards elsewhere 7000 The VFR code commonly used in Europe Refer to ICAO standards 0021 The VFR code commonly used in Germany default is set to 0021 at time of installation 7500 Hijack code Aircraft is subject to unlawful interference Page Date 31 March 2009 916 3 Section 916 Pilot s Operating Handbook BENDIX KING KT 76A Transponder XTRA EXTRA 300L 7600 Loss of communications 7700 Emergency 7777 Military interceptor operations Never squawk this code 0000 Military use Not enterable Avoid selecting code 7500 and all codes in the 7600 7777 range These trigger special indicators in automated facilities Only the code 7500 will be decoded as the hijack code An aircraft s transponder code if available is utilized to enhance the tracking capabilities of the ATC facility therefore care should be taken when making routine code changes 916 1 2 REPLY LIGHT During normal operation the flashing Reply Light indicates thatthe KT 76A is functioning properly and replying to interrogations from ground radar Interrogations occur at 10 15 second intervals corresponding to each radar sweep Frequently the reply light will blink almost continuously meaning that the transponder is responding to interrogations from several radar stations 916 1 3 TESTING THE KT 76A Allow a warm up time of about 25 sec before testing t
229. ol input NORMAL PROCEDURES Check rudder control system for impeccable easy operation during preflight inspection For that purpose the pedals have to be adjusted to a position which allows full control inputs of rudder and aileron simultaneously as well as full rudder control input in conjunction with full applied brakes the pedals may be stepless adjusted inflight independently by two switches located on the instrument panel Pay attention to symmetrical adjustment of left and right pedal PERFORMANCE Not affected WEIGHT AND BALANCE Not affected DESCRIPTION OF THE SYSTEM The optional electrical pedal adjustment system which is guided on slide tubes replaces the rear mechanical rudder pedal adjustment Such a pedal system consists of a foot rest and the rudder pedal itself including brake pedal and brake cylinder An S shaped cable leader is attached to the rudder pedal through which the control cable runs from the rudder actua tor arm to the front cable attachment at the steel frame The connection to the front seat pedals is realized by a further cable which is fixed to the control cable by two Nicopress oval sleeves The stepless pedal adjustment is realized by electromechanical actuators which are controlled separately by switches on the rear instrument panel refer to figure below The total travel of the system is limited to 6 3 by a front and a rear stop switch at the slide tube Page Date 20 April 2002 902 3
230. ommunications 7700 Emergency Page Date 31 March 2009 920 5 Section 920 Pilot s Operating Handbook BECKER BXP 6401 Transponder XTRA EXTRA 300L 7777 Military interceptor operations Never squawk this code 0000 Military use Not enterable Avoid selecting code 7500 and all codes in the 7600 7777 range These trigger special indicators in automated facilities Only the code 7500 will be decoded as the hijack code An aircraft s transponder code if available is utilized to enhance the tracking capabilities of the ATC facility therefore care should be taken when making routine code changes NOTE Unintentional transmission of an emergency code is prevented in that the transponder replies are inhibited whilst the code is being set This applies particularly where the new code is being set in the ON or ALT modes Also if a special code is called up no transponder reply takes place during the period in which the previous code can be reactivated approximately 3 seconds 920 1 5 SQUAWK IDENT After a squawk ident request from ATC press Ident button IDT D briefly This transmits an additional special pulse SPI for approx 18 seconds which enables the aircraft to be clearly identified on the radar screen of the controller Idt appears in the bottom line of the LC display during this time 920 1 6 SELFTESTS OF THE UNIT BITS The following different tests are integrated in the transponder or can be trigger
231. on equipment according to the requirements of the Air Traffic Radar Beacon System ATCRBS Its functionality includes replying to ATCRBS Mode A and C and Mode S interrogations The Mode S function will allow the ground station to individually select the aircraft by its Aircraft Address assigned to the aircraft by the aviation agency Itoperates onradar frequencies receiving ground radar interrogations at 1030 MHz andtransmitting a coded response of pulses to ground based radar on a frequency of 1090 MHz The GTX 330 15 equipped with IDENT capability that activates the Special Position Identification SPI pulsefor 18 seconds Mode S transmit receive capability also requires 1090 MHz transmitting and1030 MHz receiving for Mode S functions In addition to displaying the code reply symbol and mode of operation the GTX 330 screen will display pressure altitude and timer functions The displayed pressure altitude may not agree with the aircraft s baro corrected altitude under non standard conditions The unit also features flight timers The Traffic Information Service TIS is not available in this installation NOTE The GTX330 owner accepts all responsibility for obtaining the proper license before using the transponder The coverage you can expect from the GTX 330 is limited to line of sight Low altitude or aircraft antenna shielding by the aircraft itself may result in reduced range Range can be improved by climbing to a higher altitud
232. on or the FID button again The FID code is stored in the external aircraft connector a Factory setting for the FID 2222227 b The authorized service station should program a default FID that can be the tail number of the aircraft The pilot has to change the FID manually if necessary 913 1 3 ERROR REPORTING FAULT CODES Thetransponder s reception transmission altitude and power supply are monitored periodically This self testing routine is permanently active in the background If any error occurs due to an internal malfunction or from an external disturbance at the antenna the transponder changes to the Standby Mode and 1 displayed on the lowestline Additionally the result of the internal analysis are displayed in the second line LIST OF POSSIBLE ERRORS 1 ANT will appear if the antenna is defective e g broken cable 2 FLerr instead of the altitude appears on the display if there is an error with the altimeter or if the aircraft is outside the altitude range FL 010 to FL350 If the mode ACS was active before it will change to mode A S automatically 3 DC for a faulty transmitter power supply 4 FPG for internal communication errors 5 will appear for transmitter error In this case the unit will change to STBY and will stop all transmission Page Date 15 December 2005 913 7 Section 913 Pilot s Operating Handbook FILSER TRT 800 Transponder XTRA E
233. ontal line may be flown with any speed between Vs and Vye 4 10 Page Date 16 March 2009 Pilot s Operating Handbook Section 4 EXTRA 300L XTRA Normal Procedures Segmentline 45 climbing The plane will follow the line at max power The speed will not decrease below 80 KIAS 148 km h Segment 90 up Any entry speed may be used Out of a horizontal pull up at 200 KIAS 370 km h the vertical penetration will be 2 500 ft The speed will gradually decrease to 0 NOTE In extremely long lines a RPM decay may occur This is related to a loss of oil pressure Positive g s should be pulled immediately in order to protect the engine Oil pressure will return immediately Segment line 45 diving Throttle must be reduced in order to avoid exceeding Vye Segment lin 90 diving Throttle must be reduced to idle in order to avoid exceeding Vye Above segments may be filled up with aileron rolls on snap rolls Watch V 158 KIAS 293 km h for aileron rolls with max deflection Snap rolls should not be performed at speeds above 140 KIAS 259 km h Segment 1 4 loop climbing The minimum recommended speed is 100 KIAS 185 km h If the maneuver is to be followed by a vertical line a higher entry speed is required depending on the expected length of the line A complete loop can be performed at speeds above 100 KIAS 185 km h NOTE Since the maximum horizontal speed is 185 KIAS 3
234. open the canopy from inside proceed as follows Pull together the interior locking handles of the front or rear seat and lift canopy to the right The canopy strap will limit the opening angle To lock the canopy pull together the interior locking handles and then release To open the canopy from the outside use the aft interior handles by reaching through the small window bad weather window and proceed as mentioned above Generally the emergency operation is equal to the normal procedure When opening the canopy in normal flight the low pressure over the canopy will canopy fully open immediately However complete jettison of the canopy is possible In this case the canopy can be finally unlatched at its RH hinge line by the following action push canopy slightly forward while opening Page Date 31 March 2009 7 9 Section 7 Pilot s Operating Handbook Description and Operation of Aircraft and Systems lt s X TRA EXTRA 300L 7 10 POWERPLANT 7 10 1 ENGINE The power plant consists of one Textron Lycoming six cylinder horizontally opposed aircooled direct drive fuel injection engine type with inverted oil system The rated maximum T O Power is 300 HP at 2700 RPM Engine specification a Textron Lycoming AEIO 540 L1B5 b Textron Lycoming AEIO 540 L1B5D For the present TBO refer to latest issue of Textron Lycoming SERVICE LETTER No L 201 The AEIO 540 L1B5 D engine is equipped with special antivibra
235. ot s Operating Handbook Section 7 EXTRA 300L Description and Operation of Aircraft and Systems 7 13 CABIN ENVIRONMENT CONTROL A ventilation system in the canopy on the left side is provided for the supply of fresh air to the cabin Left and right at the rear seat are eyeball type adjustable vents Page Date 20 April 2002 7 15 Section 7 Pilot s Operating Handbook Description and Operation of Aircraft and Systems lt X TRA EXTRA 300L Left blank intentionally 7 16 Page Date 20 April 2002 Set ce tes XTRA SECTION 8 HANDLING SERVICING AND MAINTENANCE TABLE OF CONTENTS Paragraph Page 8 1 INTRODUCTION me 3 8 3 8 2 AIRPLANE 5 4 4 1 1221 8 3 8 3 PILOT CONDUCTED PREVENTIVE MAINTENANCE 8 3 8 4 ALTERATIONS OR REPAIR u III I 1 8 3 8 5 T 8 4 8 6 GROUND HANDLING n 8 4 Page Date 20 April 2002 8 1 Section 8 asad Pilot s Operating Handbook Handling Servicing and Maintenance EXTRA 3001 blank intentionally 8 2 Page Date 20 April 2002 Pilot s Operating Handbook Section 8 EXTRA 300L XTRA Handling Servicing and Maintenance SECTION 8 HANDLING SERVICING AND MAINTENA
236. ow alllocalor national regulations for testing of ELT s CAUTION Do not allow test duration to exceed 5 seconds A false alarm may be generated Any time the ELT is activated itis transmitting a 121 5 MHz distress signal After approximately 50 seconds a 406 MHz distress signal is transmitted and is considered valid by the satellite system Whenever the ELT is switched from ON to ARM a 406 MHz signal is transmitted however itis specially coded as a self test signal that is ignored by the COSPAS SARSAT satellites 926 8 2 SELFTEST Tune areceiver usually the aircraft radio to 121 5 MHz ELT aircraft panel switch for about 1 second then back to the position The receiver should voice about audio sweeps e At turn off back to ARM state the panel LED should present 1 pulse buzzer will not sound for 1 pulse If more are displayed determine the problem from the list below 1 Flash Indicates that the system is operational and that no error conditions were found 3Flashes Bad load detected Detects open or short condition on the antenna output or cable These problems can probably be fixed by the installer Check that the RF cable is connected and in good condition Perform continuity check of center conductor and shield Check for a shorted cable Check for intermittent connection in the RF cable 926 6 Page Date 19 April 2012 Pilot s Operatin
237. own entry Returns cursor to the fourth code digit within five seconds after entry 8 Reduces Contrast and Display Brightness when the respective fields are displayed if manual control is selected in the installation configuration and enters the number eight into the Count Down timer 9 Increases Contrast and Display Brightness when the respective fields are displayed if manual controlis selected inthe installation configuration and enters the number nine intothe Count Down timer 923 1 4 FUNCTIONDISPLAY PRESSURE ALT Displays the altitude data supplied to the GTX 328 in feet hundreds of feet i e flight level or meters dependent upon installation configuration FLIGHT TIME Timer start is configured as either Manual or Automatic When Manual displays the Flight Time controlled by the START STOP and CLR keys When Automatic the timer begins when take off is sensed Page Date 5 December 2008 923 5 Section 923 Pilot s Operating Handbook GARMIN GTX 328 Transponder XTRA EXTRA 300L ALTITUDE MONITOR The ALTITUDE MONITOR function is not available in this installation OAT DALT The OAT DALT function is not available in this installation no temperature input COUNT UP TIMER Controlled by the START STOP and CLR keys Pressing the CLR key zeros the display COUNT DOWN TIMER Controlled by START STOP CLR and CRSR keys The initial Count Down time is entered with the 0 9 keys Pr
238. ps and GRP laminates The shell is built using honeycomb sandwich with GRP laminates Deviating from the other control surfaces the spar webs of the surfaces of the elevator is built by CRP On the R H elevator half a trim tab is fitted with two hinges The control surfaces are mounted in spherical bearings exception Trim tab To prevent flutter rudder and elevator are mass balanced The balance weight for the rudder is installed in the rudder tip while the balance weight for the elevator is mounted on the elongated center bracket of the elevator extending into the fuselage 7 4 Page Date 31 March 2009 Pilot s Operating Handbook Section 7 EXTRA 300L X TRA Description and Operation of Aircraft and Systems 7 5 FLIGHT CONTROL SYSTEM 7 5 1 PRIMARY CONTROL SYSTEM The EXTRA 300 L is standard equipped with full dual primary flight controls including conventional stick type control columns and adjustable rudder pedals The primary control surfaces are operated through a direct mechanical linkage 7 5 2 LONGITUDINAL FLIGHT CONTROL SYSTEM The two control columns are interconnected by a torque tube The control movements are from there transferred to the elevator by a push rod 7 5 3 LATERAL FLIGHT CONTROL SYSTEM Push and pull rods are connected by sealed ball bearings from the torque tube to the ailerons The ailerons are statically as well as dynamically balanced dynamically with spades The ailerons are supported by lubri
239. pue dn 19 1 5591 1 28 191 1909 00 0065 OOLL 000 qi 7602 066 suonipuoo 006 008 002 009 00S 007 006 000 00 0 5 77 lt e c 9 e4nje1eduie apis no Ov 06 00 OL 0 0 02 O OF 922 5 Page Date 5 December 2008 EXTRA 300L Pilot s Operating Handbook XTRA Center Tank Increased Capacity 922 5 3 Endurance Section 922 u 9 1 apis no ose 00 OZ 00 Ov 02 OZ OL 0 OL OZ O Ot u 06 c lt 19 9069 eunjejeduie pisjno 55914 0008 esini2 5 o gt c Gp jo 146 e 6 7 12 Sse pue dn 61 19 5591 126 1 29 10n 190 ai 7602 056 1 suonpuo Page Date 5 December 2008 922 6 Pilot s Operating Handbook EXTRA 300L XTRA Section 922 Center Tank Increased Capacity 9226 WEIGHTANDBALANCE LOADING WEIGHTS AND MOMENTS TOTAL FUEL CAPACITY 189 L 49 9 US gal ACRO CENTER TANK L kg US gal Ib 65 143 144 31 8 18 0 39 7 21 6 47 6 252 556 28 8 63 5 324 71 4 36 0 79 3 39 6 87 3 43 2 95 2 46 8 103 2 49 7 109 6
240. r the Count Down timer andcancels transponder code entry Returns cursor to last code digit within five seconds after entry Selects changeable fields in Configuration Mode CLR Resets the Count Up and Count Down timers Cancels the previous keypress during code selection and Count Down entry Returns cursor to last code digit within five seconds after entry Used in Configuration Mode 8 Reduces Contrast and Display Brightness when the respective pages are displayed and enters the number eight into the Count Down timer Used in Configuration Mode 9 Increases Contrast and Display Brightness when the respective pages are displayed Also enters the number nine into the Count Down timer Used in Configuration Mode 915 1 4 FUNCTION DISPLAY PRESSURE ALT Displays the altitude data supplied to GTX 330 in feet hundreds of feet i e flight level or meters depending on configuration An arrow to the right of the altitude indicates that the airplane is climbing or descending Page Date 15 December 2005 915 5 Section 915 Pilot s Operating Handbook GARMIN GTX 330 Transponder XTRA EXTRA 300L FLIGHT TIME Displays the Flight Time controlled by the START STOP and CLR keys when Automated Airborne Determination is configured as normal ALTITUDE MONITOR The ALTITUDE MONITOR function is not available in this installation OAT DALT The OAT DALT function is not available in this installation no temperatur
241. r tube since the latter is safeguarded by cavity protection circuit which also requires approx 60s to warm up 2 Turn mode switch as far as it will go to TEST key position in which the transponder simulates interrogation prompting a reply The reply indication is given by the reply lamp illuminating 918 1 2 SQUAWK SELECTION Squawk selection is done with the four rotating knobs to provide 4096 identification codes Important Codes 1200 The VFR code for any altitude in the US Refer to ICAO standards elsewhere 7000 The VFR code commonly used in Europe Refer to ICAO standards 0021 The VFR code commonly used in Germany default is set to 0021 at time of installation 7500 Hijack code Aircraft is subject to unlawful interference 7600 Loss of communications 7700 Emergency 7777 Military interceptor operations Never squawk this code 0000 Military use Not enterable Avoid selecting code 7500 and all codes in the 7600 7777 range These trigger special indicators in automated facilities Only the code 7500 will be decoded as the hijack code An aircraft s transponder code if available is utilized to enhance the tracking capabilities of the ATC facility therefore care should be taken when making routine code changes 918 4 Page Date 15 December 2005 Pilot s Operating Handbook 2 Section 918 XTRA BECKER ATC 2000 Transponder EXTRA 300L 918 1 3 MODE A OPERATION 1 Activate the transponder on ATC requ
242. ration and Installation Manual Section Part 3 PN 60 297 32 This RPM setting is not allowed for airplanes equipped with a 3 blade propeller Type MT V 9 B C C 198 25 operated inthe normalcategory in which noise protection requirements must be complied with Page Date 19 April 2012 921 7 EXTRA 300L Pilot s Operating Handbook XTRA 921 5 2 Range Configuration 1 Lycoming AEIO 580 B1A Engine Section 921 WN 5 pis no 007 008 07 06 00 OL 0 0 0 0 Or INN lt 19 29 sseJd 0008 951019 gt gt ee e c jo e 10 8 1 559 pue dn 16 ssa y 1 LZ 10n 7602 096 1 suonipuo 006 000 00 000 006 008 004 009 005 007 006 000 00 Page Date 19 April 2012 921 8 Section 921 Lycoming AEIO 580 B1A Engine Pilot s Operating Handbook EXTRA 300L XTRA 921 5 3 Endurance Configuration 1 1 5591 u ooe 052 0 Gy Gp jo e 10 e 79 02 u lt JeMog 9579 9o b pisino
243. re RICH 4 Boost pump ON 5 Ignition switch BOTH or START if propeller has stopped 3 4 Page Date 16 March 2009 EXTRASOOL XTRA Section 3 Emergency Procedures 3 2 4 OILSYSTEM MALFUNCTION If oil pressure indicates low If oil pressure is not regained then 1 Airspeed 2 Throttle 3 Engine oil temperature 4 Land WARNING Apply positive g 80 KIAS 148 km h REDUCE TO IDLE OBSERVE INDICATION ASAP If oil pressure drops to 0 psi kPa the propeller pitch changes automatically to coarse high pitch with a corresponding decrease in RPM 3 2 5 ALTERNATOR FAILURE An alternator failure is indicated by the red light of the low voltage monitor If red light illuminates 1 Alternator 2 Low voltage monitor 3 Red light off If red light illuminates again 4 Land 3 3 FORCED LANDINGS SWITCH OFF AND ON CHECK INDICATION CONTINUE FLIGHT AS SOON AS PRACTICAL 3 3 1 EMERGENCY LANDING WITHOUT ENGINE POWER Seat belts shoulder harnesses Airspeed Mixture Fuel shutoff valve Ignition switch Master switch Touchdown Brakes O gt G N SECURE 80 KIAS 148 km h IDLE CUT OFF OFF Pull amp Turn OFF OFF SLIGHTLY TAIL LOW OPTIMUM BRAKING 3 3 2 PRECAUTIONARY LANDING WITH ENGINE POWER 1 Seat belts shoulder harnesses Airspeed Selected field Co Master switch Touchdown Ignition switch Mixture Fuel shutoff valve
244. re should be taken not to select the code 7500 and all codes in the 7600 7777 range which trigger special indicators in automated facilities Only the code 7500 will be decoded as the hijack code An aircraft s transponder code if available is utilized to enhance the tracking capabilities of the facility therefore care should be taken when making routine code changes STANDBY MODE The standby mode is activated by pressing the MODE button once This sets in the mode indicator field The transponder will now only reply to direct addressed Mode S interogations The squitter stays active at a lower rate ALTITUDE OFF Switching off altitude reporting will be necessary if the ATC controller requests it For switching off altitude reporting the MODE button has to be pressed until A S is displayed The altitude display shows FL to indicate that the altitude reporting is not active Now the transponder will reply on Mode C interrogations with Mode C frames only and Mode S interrogations with FL000 0000 instead of the actual altitude IDENT Pressing the IDT push button causes the special position identification pulse SPI to be appended to the Mode A replies for a period of 18 seconds and sets IDT in the display LOW POWER SUPPLY If the power supply to the transponder drops below 10 Volts the appears and starts flashing DISPLAYING AIRCRAFT ADDRESS AND FLIGHT IDENTIFICATION By pressing t
245. ress assigned to the aircraft by the aviation agency Itoperates onradar frequencies receiving ground radar interrogations at 1030 MHz andtransmitting a coded response of pulses to ground based radar on a frequency of 1090 MHz The GTX 328 is equipped with IDENT capability that activates the Special Position Identification SPI pulsefor 18 seconds Mode S transmit receive capability also requires 1090 MHz transmitting and1030 MHz receiving for Mode S functions In addition to displaying the code reply symbol and mode of operation the GTX 328 screen will display pressure altitude and timer functions The displayed pressure altitude may not agree with the aircraft s baro corrected altitude under non standard conditions The unit also features flight timers The Traffic Information Service TIS is not available in this installation NOTE The GTX328 owner accepts all responsibility for obtaining the proper license before using the transponder The coverage you can expect from the GTX 328 is limited to line of sight Low altitude or aircraft antenna shielding by the aircraft itself may result in reduced range Range can be improved by climbing to a higher altitude It may be possible to minimize antenna shielding by locating the antenna where dead spots are only noticed during abnormal flight attitudes CAUTION The GTX 328 should be turned off before starting or shutting down aircraft engine The GTX 328 Transponderis automatically pow
246. restore the previous identification code When TST mode pushing the VFR button will display the software revisions on the Altitude window and Ident window for a minimum of 4 seconds FLT ID When in FLT ID mode the flight ID can be entered or modified by rotating the FLT ID knob 2nd ATCRBS Code Selector Knob to select desired character for each digit selected by the CRSR knob Once the CRSR and FLT ID knobs have been idle for 5 seconds or the Function Selector Knob has been turned to the SBY position the flight ID will be saved CRSR Whenin FLT ID mode rotating the CRSR knob 2 1st ATCRBS Code Selector Knob will position the cursor under the character of the flight ID to be changed Page Date 31 March 2009 917 5 Section 917 Pilot s Operating Handbook BENDIX KING KT 73 Transponder XTRA EXTRA 300L BRT When in TST mode rotating the BRT knob 4th ATCRBS Code Selector Knob will manually adjust the display brightness Clockwise rotating will increase display brightness and counterclockwise will decrease display brightness The brightness of the display is determined by a photocell relative to the programmed or manual adjusted brightness level 917 1 4 FUNCTIONDISPLAY FL When the ALT mode is selected the letters FL will be illuminated The pressure altitude data supplied to the KT 73 is displayed in hundreds of feet i e Flight Level on the left side of the display the altitude window In addit
247. rks to stop the spin Power idle Kick rudder to the heavier side this will always be against spin direction Take hands off the stick The spin will end after 1 2 turn The plane will be in a steep dive in a side slip Recovery to normal flight can be performed easily NOTE After six turns of spinning the altitude loss including recovery is 2000 ft 4 12 Page Date 20 April 2002 Pilot s Operating Handbook XTR A EXTRA 300L Paragraph 5 1 5 1 1 5 1 2 5 1 3 5 2 5 3 5 4 5 5 5 6 5 7 5 8 5 9 5 10 5 11 SECTION 5 PERFORMANCE Table of Contents Page GENERAL 5 3 Performarice uu u u u uu 5 3 Definitions ot Ili 5 3 Sample PLO DIS Masts once sade 5 3 ISA CONVERSION is ccc 5 5 AIRSPEED CALIBRATION M M 5 6 STALL SPEED u uu un aola 5 7 TAKE OFF PERFORMANCE eh dann icone nain aa ana ans 5 8 RATE OF CLIMB u u uuu u 5 9 TIME TO CLIMB FUEL TO 5 10 RANGE AND ENDURANCE
248. rmal Climb Speed 100 185 105 194 110 204 Max Cruise 185 343 185 343 185 343 Landing Approach 80 148 85 157 90 167 onFinal 72 133 74 137 78 144 Go Around Speed 90 167 95 176 100 185 Recommended Airspeed For Flight In Rough Air max 158 293 158 293 140 259 Max Demonstrated Cross Wind Component 15kts 27 15 kts 27 15 kts 27 4 0 2 CHECKLIST AND PROCEDURES This handbook contains the checklist and procedures to operate the aircraft in normal and acrobatic operation The pilot should be familiar with all procedures contained in this Pilot s Operating Handbook which must be carried on board The pilot has to comply with the checklist for daily check and inspections see Section 8 Handling Servicing and Maintenance Page Date 19 April 2012 4 Section 4 Normal Procedures XTRA Pilot s Operating Handbook EXTRA 3001 4 1 PREFLIGHTINSPECTION 4 1 1 EXTERIOR INSPECTION ILLUSTRATION 4 1 2 GENERAL Visually check airplane for general condition during walk around inspection Perform exterior check as outlined in the picture above in counterclockwise direction 4 2 CHECKLIST PROCEDURES 1 Cockpit NOOR GQ Pilot s Operating Handbook Airplane weight and balance lgnition switch Master switch Fuel quantity indicators Master switch Fuel selector NOTE AVAILABLE CHECKED OFF ON CHECK OFF ACRO
249. rnator 11 Wingtip position Strobe lights DRAIN FORAT LEAST 4 SECONDS TO CLEAR SUMP OF POSSIBLE WATER CHECK CLOSED DRAIN FORAT LEAST 4 SECONDS TO CLEAR SUMP OF POSSIBLE WATER CHECK CLOSED DRAIN FORAT LEAST 4SECONDS TOCLEAR FILTER OF POSSIBLE WATER CHECK CLOSED CHECK FOR DAMAGE AND SECURE ATTACHMENT CHECK CHECK CHECK REMOVE CHECK CHECK COMPLETE COMPLETE COMPLETE ADJUST AND LOCK CLOSE AND LOCK CHECK ON OFF OFF ON ON Page Date 20 April 2002 Section 4 Pilot s Operating Handbook Normal Procedures lt s XTRA EXTRA 300L 4 3 STARTINGPROCEDURES 4 3 1 COLDENGINES The following starting procedures are recommended however the starting conditions may necessitate some variation from these procedures 1 Perform pre flight inspection 2 Set propeller governor control to High RPM position 3 Open throttle approximately 1 4 travel 4 Turn boost pump ON 5 Move mixture control to FULL RICH until a slight but steady fuel flow is noted approximately 3 to 5 seconds and return mixture control to IDLE CUT OFF Turn bost pump OFF 6 Engage starter 7 When engine fires release the ignition switch back to BOTH 8 Move mixture control slowly and smoothly to FULL RICH 9 Check the oil pressure gauge If minimum oil pressure is not indicated within 30 seconds shut off the engine and determine trouble 4 3 2 HO
250. rom 2000 ft 610 m to 8000 ft 2438 m is acc to Fig 5 7 gt 4 0 0 9 min 3 1 min The Fuel to Climb from 2000 ft 610 m to 8000 ft 2438 m is gt 5 8 1 4 Liters 4 4 Liters 1 2 US Gal CRUISE Cruise Altitude and Power Setting should be determined for most economical fuel consumption and several other considerations In an altitude of 8000 ft 2438 m and a Power Setting of 65 96 a Fuel Consumption of 52 L H 13 7 US Gal H and 3 25 NM L 12 3 NM US Gal can be obtained by Fig 5 9 RANGE AND ENDURANCE Fig 5 8 presents Range and Endurance values for a T O Weight of 950 kg 2095 Ibs including fuel for warm up and Take Off from SL max continuous Power climb to cruising altitude and a reserve of 21 liter 5 5 US Gal for 45 minutes with 4596 Power 5 5 liters 1 45 US Gal unusable fuel is taken into account For the sample problem appr Total Fuel 171L 45 1 US Gal Warm Up amp T O 5L 1 3 US Gal Reserve 21 L 5 54 US Gal Unusable Fuel 55L 1 45 US Gal Usable Fuel 139 5L 36 8 US Gal Range 415 NM 768 km Endurance 2 49 HRS 5 4 Page Date 16 March 2009 Pilot s Operating Handbook Z Section 5 EXTRA 300L 5 2 ISA CONVERSION ISA Conversion of pressure altitude and outside air temperature TEMPERRTURE F 80 40 40 80 120 16 15 14 x 19 12 a 11 T a 10 9 5 8 3 7 6
251. rs Cursor Press Freq MHz Terrain Flight to activate Small Knob Phase and Com VLOC GPS Integrity __ 088 oo Procedure Key Freq kHz Annunciator Mounting Key Screw Key Message K Navigation Source GPS VLOC or GPS PTK 92511 GPS WAASTSO C146A CLASS 3 OPERATION The Garmin GNC 420W uses GPS and WAAS within the coverage of a Space Based Augmentation System complying with ICAO Annex 10 for enroute terminal area non precision approach operations including GPS GPS and RNAV approaches and approach procedures with vertical guidance including _LNAV VNAV and Navigation is accomplished using the WGS 84 NAD 83 coordinate reference datum GPS navigation data is based upon use of only the Global Positioning System GPS operated by the United States of America 925 1 2 CLASSIIOCEANIC REMOTE AND OTHER OPERATIONS The Garmin GNC 420W as installed has been found to comply with the requirements for GPS primary means of Class navigation in oceanic and remote airspace when used in conjunction with WAAS Garmin Prediction Program part number 006 A0154 03 Oceanic operations are supported when the GNC 420W annunciates This provides an alarm limit of four NMI and a mask angle Page Date 31 March 2009 925 3 Section 925 Pilot s Operating Handbook GARMIN GNC 420W XTRA EXTRA of five degrees The 420W also has the ability to predict RAIM avail
252. ru 905 2 20 April 2002 15 December 2005 905 3 thru 905 4 15 December 2005 m 16 2009 905 5thru 905 6 20 April 2002 212 P 19 April 2012 906 1 thru 906 2 20 April 2002 15 December 2005 906 3 thru 906 6 19 April 2012 2 14 16 March 2009 907 1 uu assaka 16 March 2009 3 1 thru 3 2 20 April 2002 907 2thru 907 3 20 April 2002 ee 31 March 2009 907 4 thru 907 6 16 March 2009 3 4thru 3 5 16 March 2009 908 1 thru 908 2 20 April 2002 BG 20 April 2002 908 3 thru 908 8 16 March 2009 E 16 March 2009 5009 M 20 September 2006 31 March 2009 909 2 20 April 2002 31 March 2009 909 3 iiio 31 October 2013 saei te eene dia 20 April 2002 eee e 16 March 2009 4 3 thru 4 4 19 April 2012 909 5 thru 909 8 20 September 2006 4 5thru 4 6 20 April 2002 910 1 thru 910 2 20 April 2002 d UE 16 March 2009 910 3thru910 5 16 March 2009 4 8 p 31 March 2009 910 6thru910 8 20 April 2002 4 9thru 4 11 16 March 2009 911 1thru911 2 20 April 2002 412 P 20 April
253. selected code is then displayed After 3 seconds the displayed code gets active and overwrites the previously set reply code 2 Pressing push button J again within 3 seconds reactivates the previously set reply code NOTE When the unit is delivered the VFR button is not assigned a code This means that if this button is pressed for 0 5 seconds is shown in the code display and the transponder then switches back to the previously active code 920 1 10 CONFIGURATION MODE The configuration mode is available from SBY mode only To get into configuration mode press button SEL turn rotary encoder B until CFG appears in the bottom row of the display Refer to BECKER s Pilot s Guide for available options 920 2 LIMITATIONS Not applicable 920 3 EMERGENCY PROCEDURES 920 3 1 IMPORTANT CODES 7600 Loss of communications 7500 Hijacking 7700 Emergency All secondary surveillance radar sites are ready to receive this code at all times See the Airman s Information Manual AIM for a detailed explanation of identification codes 920 4 NORMAL PROCEDURES Not applicable 920 5 PERFORMANCE Not applicable 920 10 Page Date 31 March 2009 52 211 Handbook SECTION 921 LYCOMING AEIO 580 B1A ENGINE Table of Contents Paragraph Page 921 1 GENERAL u 921 3 921 2 LIMITATIONSu 921 3 921 2 1 Engine Lima uu ug
254. smission Ensure that whip antenna is clear of obstruction 904 4 Page Date 20 April 2002 Pilot s Operating Handbook Section 904 EXTRA 300L X TRA Emergency Locator Transmitter C Operating of the ELT in the portable mode After forced landing or aircraft accident it may be desirable to use the transmitter in the portable mode Various reasons may necessitate this such as Broken or disabled whip antenna D REMOVE ELT FROM A C Severed whip antenna cable Danger of fire or explosion in aircraft Temperature extremes in aircraft Poor transmitting location D Removal of ELT from aircraft NOTE Accomplish as quickly as possible to resume or start emergency signal Turn the unit master switch to OFF position Disconnect whip antenna cable and remote switch cable Turn winged nut on rear bracket clip to release transmitter remove ELT Remove the telescope antenna from the stowage clips and insert into the ANT recepta cle Extend antenna fully CAUTION 5 Turn unit master switch to ON position Do not use the AUTO position Best transmission may be obtained by Keeping antenna vertical Standing transmitter upright on a metallic surface such as an aircraft wing or stabilizer If terrain prohibits good transmission such as a deep valley or canyon place the transmit ter on the high ground or hold in hand on hig
255. spring in a tail wheel design The main wheels have a size of 5 5 50 and they are equipped with hydraulic disc brakes The tail wheel has a solid rubber tire with full swivel capability Page Date 20 April 2002 Pilot s Operating Handbook Section 7 EXTRA 300L X TRA Description and Operation of Aircraft and Systems 7 8 SEATS SEAT BELTS The seats are ergonomically shaped composite designs The rear seat angle can be adjusted on the ground with 2 quickpins there are different seat angle possibilities The back rest is also adjustable on the ground in different positions and angle The rear pedal to seat distance can be varied in different positions In the front cockpit there is no possibility to adjust either the pedals nor the seat The seat belt assembly consists of a left and a right shoulder strap two left and two right lap belts and a negative g strap All belts are adjustable As each lap belt features a single point release they are redundant for safety during aerobatic maneuvers If one release is opened unintentionally the second one guarantees full safety For safe operation the releases are arranged in a way that one has to be closed to the right side the other one to the left During acrobatic maneuvers the seat belt system should be tightened firmly 7 9 CANOPY The canopy is manufactured in one section and can be manually operated by interior locking handles located on the left side on the canopy To
256. t control knob until the HDG field is enabled for editing ROTATE the knob to the desired setting Altitude Bug Set To set the altitude bug repeatedly PUSH the right control knob until the ALT field is enabled for editing ROTATE the knob to the desired setting Barometric Pressure Set To set the barometric pressure repeatedly PUSH the right control knob until the BARO field is enabled for editing ROTATE the knob to the desired setting NOTE Cross check the barometric pressure setting against the primary altimeter whenever the value is adjusted on the EFD1000 PILOT PFD Course Set Tosetthe course repeatedly PUSHthe left control knob until the CRS field is enabled for editing ROTATE the knob to the desired setting Page Date 31 March 2009 924 7 Section 924 mE Pilot s Operating Handbook ASPENEFD1000PILOT PFD XTRA EXTRA Indicated Airspeed Bug Set To set the indicated airspeed bug repeatedly PUSH the left control knob until the IAS field is enabled for editing ROTATE the knob to the desired setting 924 7 7 KNOB SYNC FUNCTION Editable fields may be synchronized as a function of data type as described in Table 1 below Whenever a control knob 15 held for approximately one second the active data type will be sync d as follows Right Knob SYNC Behavior The airspeed bug is The heading bug is set set to the current to the current heading The altimeter bug is set to the current altitude
257. tch the transponder to ALT using mode switch A 3 The transponder replies using the code set and in response to mode C requests it tansmits the flight level of the aircraft to ATC A triangle on the left next to the code signals the transponder replies SQUAWK IDENT After a squawk ident request from ATC press Ident button IDT D briefly This transmits an additional special pulse SPI for approx 18 seconds which enables the aircraft to be clearly identified on the radar screen of the controller Idt appears in the bottom line of the LC display during this time TEST The following different tests are integrated in the transponder or can be triggered at the transponder Automatic switching on test in which the display E is flashing with all digits for 3 seconds The unit is subject to a self test in this time A permanent test runs in the background of the transponder operation The built in FPGA organizes the required resources for this The transmitter recognizes a missmatching or own abnormal behavior and delivers an alarm signal to the FPGA Page Date 15 December 2005 919 7 Section 919 Pilot s Operating Handbook BECKER 4401 Transponder XTRA EXTRA 300L 3 Afurther test of the unit is triggered if the VFR1 button F and VFR2 button G are pressed simultaneously At this test all segments must flash into display E as long as the buttons are pushed Additional the transmitter and evalua
258. tem ATCRBS Its functionality includes replying to ATCRBS Mode A and C and Mode S interrogations The Mode S function will allow the ground station to individually select the aircraft by its Aircraft Address assigned to the aircraft by the aviation agency Encoding Altimeter Ident Reply Function Altitude Window Window Indicator Selector Pushbutton Photocell VFR Fail Button Indication 4 ATCRBS Code Selector Knobs Itoperates onradar frequencies receiving ground radar interrogations at 1030 MHz andtransmitting a coded response of pulses to ground based radar on a frequency of 1090 MHz The 73 is equipped with ident capability that activates the Special Position Identification SPI pulse for 18 seconds In addition to displaying the code reply symbol and mode of operation the KT 73 screen will display pressure altitude The displayed pressure altitude may not agree with the aircraft s baro corrected altitude under non standard conditions The Traffic Information Service TIS and Automatic Dependent Surveillance Broadcast ADS B is not available in this installation NOTE The KT 73 owner accepts all responsibility for obtaining the proper license before using the transponder The coverage you can expect from the KT 73 is limited to line of sight Low altitude or aircraft antenna shielding by the aircraft itself may result in reduced range Range can be improved by climbing to a higher altitude It may be possib
259. ter Amber flag presented on the upper right corner of the display to indicate the aircraft is reaching steady or deviating flashing from the preselected altitude 924 7 13 MAIN MENU OPERATION MENU CONTROLS The EFD1000 PILOT PFD Main menuis used to adjust various system configuration settings and preferences To selectthe Main Menu press the MENU button onthe right side of the display bezel To leave the menu press the MENU button again Menu items are shown exclusively in the lower half of the EFD1000 PILOT PFD display in the region below the data bar MAIN MENU NAVIGATION Once the Main menu 15 activated rotating the lower right control knob selects between the various menu pages The current menu page is indicated by the page name and legend 01 and by the location of the green segment within the segmented menu navigation bar displayed at the bottom of the display CONFIGURING MENUITEMS Each menu page shows a series of menu selections adjacent to the right bezel line select keys Editable menu selections are indicated by white text while status only or non editable items are shown in green Items that have been inhibited from editing are shown in gray Pressing a line select key adjacent to an editable field enables the item for editing indicated by showing the editable value in magenta Rotating the lower right control knob adjusts the editable value Changes are effective immediately To exit the edit mode press t