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1. 917 6 917 1g Failure etu rese d vie thee Dev respec d de Ead Cm 917 7 917 2 Mi igr ype lc 917 7 917 3 EMERGENCY PROCEDUBRES 917 7 917 4 NORMAL PROCEDURES 917 7 917 5 PERFORMANCE 917 7 Page Date 28 February 2006 917 1 Section 917 mE Pilot s Operating Handbook BENDIX KING KT 76A Transponder XTRA EXTRA 300 Left blank intentionally 917 2 Page Date 28 February 2006 Pilot s Operating Handbook E Section 917 EXTRA 300 XTRA BENDIX KING KT 76A 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 System ATCRBS Its functionality includes replying to ATCRBS Mode A and C and Mode 5 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 It operates on radar frequencies receiving ground radar interrogations at 1030 MHz and transmitting a cod
2. 904 6 904 8 HANDLING SERVICING AND MAINTENANCE 904 7 Page Date 20 April 2002 904 1 Section 904 IL Pilot s Operating Handbook Emergency Locator Transmitter 300 Left blank intentionally 904 2 Page Date 20 April 2002 Pilot s Operating Handbook Section 904 EXTRA 300 Emergency Locator Transmitter 904 EMERGENCY LOCATOR TRANSMITTER 904 1 GENERAL To improve the passive security the EXTRA 300 can be equipped with an optional Emer gency Locator Transmitter POINTER 3000 ELT This POINTER 3000 ELT transmits auto matically 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 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 height of the ELT unit placard below the ELT circuit breaker see Fig 1 1 CIRCUIT BREAKER 1A ELT NA 0900090909 09 9 ON Figure 1 Page Date 20 April 2002 904 3 Section 904 2 Pilot s Operating Handbook Emergency Locator Transmitter 300 904 3 EMERGENCY PROCEDURES Aircraft accident or force
3. 7 10 ccr r enr 7 11 Engine DP 7 11 ien E 7 11 Hume alee 7 11 je EE 7 12 giri Servio 7 12 Sh toff VaVe 7 12 Exhaust Systems Optional 7 12 diss expel 7 12 ELECTRICAL SYSTEM 7 13 CABIN ENVIRONMENT CONTROL 7 15 Page Date 28 February 2006 7 Pilot s Operating Handbook Description and Operation of Aircraft and Systems X TRA EXTRA 300 Left blank intentionally Page Date 20 April 2002 Pilot s Operating Handbook mE Section 7 EXTRA 300 X TRA Description and Operation of Aircraft and Systems SECTION 7 DESCPRIPTION AND OPERATION OF AIRCRAFT AND SYSTEMS 7 1 THE AIRCRAFT The aircraft EXTRA 300 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 is a light weight robust single piston engined two seat aircraft with a f
4. 1 5 1 6 H 1 5 1 7 1 5 1 8 ep Ucet 1 6 1 9 jusliejKelc ge 1 6 1 10 SECONDARY TERMINOLOGY 1 7 Page Date 28 February 2006 1 1 1 Pilot s Operating Handbook General XTRA EXTRA 300 Left blank intentionally 1 2 Page Date 20 April 2002 Pilot s Operating Handbook Z Section 1 General EXTRA 300 1 0 1 1 1 2 1 3 1 3 1 DESCRIPTION This description belongs to aircraft type EXTRA 300 with nationality and registration marks Manufacturing The airframe is built of tig welded steel tube construction Wings rudder and landing gear are manufactured of composite material The aircraft is a two seater with the rear seat instrumented for pilot in comand SPECIFICATION OF CLASS The aircraft is certified in normal and acrobatic category LBA Certificate No 1086 MANUFACTURER Manufacturer EXTRA Flugzeugproduktions und Vertriebs GmbH Flugplatz Dinslaken 46569 H nxe Federal Republic of Germany TECHNICAL DATA 3 VIEW DRAWING Page Date 28 February 2006 1 3 Section 1 General XTRA Pilot s Operating Handbook EXTRA 300 1 3 2 MAIN DATA Length He
5. 905 4 Page Date 28 February 2006 Pilot s Operating Handbook 2 Section 905 EXTRA 300 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 300 Left blank intentionally 905 6 Page Date 20 April 2002 Pilot s Operating Handbook XTR A EXTRA 300 Paragraph 906 1 906 2 906 3 906 4 906 5 906 6 906 7 906 8 SECTION 906 DIGITAL RPM INDICATOR Table of Contents Page GENERAL 906 3 B pues 906 3 EMERGENCY PROCEDURES cid acra qaa 906 3 NORMAL PROCEDURES 1acnati ruant aant hann ach senseecdneataceunadsann ceanensaunesedcessaevnentd 906 3 PERFORMANCE c 906 4 WEIGHT AND BALANCE 2 2 1 1 1 snas nass nanus sna 906 4 DESCRIPTION AND OPERATION OF THE SYSTEM 906 4 HANDLING SERVICING AND MAINTENANCE 42241221 906 6 Page Date 20 April 2002 906 1 Section 906 IL Pilot s Operating Handbook Digital RPM Indicator 300 Left blank intentionally 906 2 Page Da
6. 2006 901 1 thru 901 4 20 April 2002 2 2 litt 2 9 20 April 2002 902 1 thru 902 4 20 April 2002 2 4 thru 2 5 28 February 2006 903 1 thru 903 10 20 April 2002 rnnt 20 April 2002 904 1 thru 904 8 20 April 2002 28 2006 905 1 thru 905 2 20 April 2002 20 September 2006 905 3 thru 905 4 28 2006 20 April 2002 905 5 thru 905 6 20 April 2002 2 10 thru 2 11 28 February 2006 906 1 thru 906 6 20 April 2002 20 April 2002 907 1 thru 907 6 20 April 2002 2 13 thru 2 14 28 February 2006 908 1 thru 908 8 20 April 2002 3 1 thru 38 4 20 April 2002 909 1 20 September 2006 28 2006 909 2 20 April 2002 20 April 2002 909 3 thru 909 8 20 September 2006 tang 28 February 2006 912 1 thru 912 8 28 February 2006 3 8 20 April 2002 913 1 thru 913 8 28 February 2006 28 February 2006 914 1 thru 914 6 28 February 2006 4 2 thru 4 7 20 April 2002 915 1 thru 915 8 28 February 2006 cucine i ets 28
7. 903 3 EMERGENCY PROCEDURES 4 ta pace Ene 903 3 NORMAL PROCEDURES niea nnam nh luna n aet a uam 903 3 dsixeliule 903 3 WEIGHT AND BALANCE aa un 903 3 DESCRIPTION AND OPERATION OF THE SYSTEM 903 3 HANDLING SERVICING AND MAINTENANCE 4 4 44 12211 903 9 Page Date 20 April 2002 903 1 Section 903 IL Pilot s Operating Handbook Electronic Accelerometer EXTRA 300 Left blank intentionally 903 2 Page Date 20 April 2002 Pilot s Operating Handbook Section 903 EXTRA 300 X TRA Electronic Accelerometer 903 ELECTRONIC ACELEROMETER 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 Instrument markings Electronic Accelerometer DSA 12 red range 12g 10g y
8. 913 8 azizelll bie 913 8 Page Date 28 February 2006 913 1 Section 913 mE Pilot s Operating Handbook FILSER TRT 800 Transponder XTRA EXTRA 300 Left blank intentionally 913 2 Page Date 28 February 2006 Pilot s Operating Handbook 2 Section 913 EXTRA 300 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 5 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 Knob for 1000 Rotating knot for 1 Sguitter flag elimina Code Test Monitor Eatery flag t Displ ay Flight Level a In Flight flag Standby Code Rotating knob for 10 Rotating knob IDENT for 100 Made Select a 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 p
9. isa nn 908 4 PERFORMANCE 908 5 WEIGHT AND BALANCE ena naa aem Renan E npa 908 7 DESCRIPTION OF THE SYSTEM red ada eau na Vau nonno rm oa naa daa erunt cua 908 7 HANDLING SERVICING AND MAINTENANCE 424 1221 1 908 7 Page Date 20 April 2002 908 1 Section 908 IL Pilot s Operating Handbook Airtow Hook 300 Left blank intentionally 908 2 Page Date 20 April 2002 Pilot s Operating Handbook EXTRA 300 Section 908 Airtow Hook 908 AIRTOW HOOK 908 1 GENERAL The EXTRA 300 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 The following combinations are certified Aircraft Engine AEIO 540 L1B5 or AEIO 540 L1B5D Propeller MTV 14 B C C 190 17 Exhaust system Typ Gomolzig EA 300 606000 or standard exhaust PC 63104 with silencer NSD GO3 606500 Air tow release system according to replacement instruction UA 300 4 95 Air tow release TOST E 85 Glider MTOW of the glider 765Kg Max air towing speed of the glider min 152 Km h Air tow cable and breaking piece weak links Length of the synthetic tow between 40 and 60m Ultimate load of the air tow max 850 kp 1875 Ibs If tows with higher ultimate load are use
10. 200 15 Maximum Take Off max 5 min 2700 RPM Maximum Continuous 2400 RPM NOTE If not stated otherwise refer to Section 4 12 Acrobatic Maneuvers the aircraft may be operated in the acrobatic maneuvers up to 2700 RPM 2 6 WEIGHT LIMITS Max allowed empty weight Normal category 745 kg 1643165 Acrobatic category 1 seat 701 kg 1546lbs 2 seats 665 kg 1466lbs Max allowed T O weight Normal category 950 kg 2095 Ibs Acrobatic category 1 seat 820 kg 1808 Ibs 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 Weight forward C G rear MaxT O 950 kg 2095 Ibs 78 0cm 30 7 86 0cm 33 8 820 kg 1808 Ibs 75 0cm 29 5 89 8cm 35 3 and below Straight line variation between the stated limits 2 7 2 ACROBATIC FLIGHT 1 SEAT Max T O Weight forward C G rear C G 820 kg 1808 Ibs 75 0cm 29 5 89 8cm 35 3 and below Page Date 28 February 2006 2 5 Section 2 Pilot s Operating Handbook Limitations XTRA EXTRA 300 2 7 3 ACROBATIC FLIGHT 2 SEAT Weight forward C G rear Max T O 870 kg 76 5cm 30 1 88 5cm 34 8 1918 Ibs 820 kg 1808 Ibs 75 0cm 29 5 89 8cm 35 3 and below Straight line variation between the stated limits 2 8 ACROBATIC MANEUV
11. Particular caution must be exercised when performing maneuvers at speeds above Va 158 KIAS 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 horizontal line may be flown with any speed between and 4 10 Page Date 20 April 2002 Pilot s Operating Handbook Section 4 EXTRA 300 Normal Procedures Segment line 45 climbing The plane will follow the line at max power The speed will not decrease below 80 KIAS Segment line 90 up Any entry speed may be used Out of a horizontal pull up at 200 KIAS the vertical penetration will be 2 500 ft The speed will gradually decrease to 0 NOTE In extremely long lines an 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 V Segment lin 90 diving Throttle must be reduced to id
12. 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 0 4 Page Date 20 April 2002 Pilot s Operating Handbook Section 0 EXTRA 300 Publication Guidance 4 LOG OF EFFECTIVE PAGES Dates of issue for original and revised pages Date and sign of approval Original 5 1990 LBA approved 30 October 1990 Revision No 1 20 March 1991 LBA approved 15 May 1991 Revision No 2 21 January 1992 LBA approved 5 February 1992 Revision No 11 September 1992 LBA approved 13 October 1992 Revision No 4 3 January 1993 LBA approved 21 May 1993 Revision No 5 6 May 1994 LBA approved 6 May 1994 Revision No 6 20 December 1994 LBA approved 24 January 1995 Revision No 7 26 June 1997 LBA approved 27 August 1997 Edition No 2 s 20 April 2002 LBA approved 30 October 2002 Rev 1 2nd Ed
13. 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 28 February 2006 Pilot s Operating Handbook 2 Section 918 BECKER 2000 Transponder EXTRA 300 918 1 3 MODE A OPERATION 1 Activate the transponder request only 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 i
14. 28 February 2006 EASA Approval EASA A A 01277 Date of Approval 05 September 2006 Rev No 2 2nd Ed 20 September 2006 EASA Approval N EASA A A 01319 Date of Approval 20 November 2006 Page Date 20 September 2006 0 5 Pilot s Operating Handbook Publication Guidance EXTRA 300 LOG OF EFFECTIVE PAGES cont Page Date Page Date Titel 28 February 2006 6 4 thru 6 9 20 April 2002 20 April 2002 6 10 thru 6 14 28 February 2006 1E 28 February 2006 E ere 28 2006 0 1 thru 0 2 20 April 2002 7 0 20 April 2002 058 ies 28 February 2006 Ec ENT 28 February 2006 0 4 20 April 2002 Athr 7 9 ns 20 April 2002 0 5 thru 0 6 20 September 2006 7 10 thru 7 14 28 February 2006 28 February 2006 7 15thru 7 16 20 April 2002 coves S 20 April 2002 8 1 thru 8 4 20 April 2002 28 February 2006 e E 28 February 2006 20 April 2002 20 April 2002 enacts 28 February 2006 E e 28 February 2006 1 6 thru 1 8 20 April 2002 9 4 20 April 2002 2 28
15. 6 5 Sie M 6 7 Weight And Balance Record 6 7 LOADING WEIGHTS AND MOMENTS 6 8 WEIGHT AND MOMENT 6 9 EQUIPMENT UIST lt lt 6 10 Page Date 20 April 2002 6 1 Section 6 Weight and Balance and Equipment List XTRA Pilot s Operating Handbook EXTRA 300 Left blank intentionally Page Date 20 April 2002 Pilot s Operating Handbook Section 6 EXTRA 300 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 provided A comprehensive list of all equipment available for this aircraft is included It is the responsibility of the pilot to ensure that the aircraft is loaded properly 6 2 AIRCRAFT WEIGHING PROCEDURE The aircraft weight is determined by weighing all three wheel loads simultaneously by three scales with the aircraft levelled Upper fuselage reference line horizontal Datum line for weight arms x is the fire wall X1 distance fire wall main wheel X2 distance fire wall tail wheel XN distance fire wall item XG distance fire wall Center of Grav
16. 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 A C reply code and altitude code 919 7 919 7 RW PEDE EET LL E 919 7 Gonfiguration 919 8 LIMITATIONS 2 919 8 EMERGENCY PROCEDURES 919 8 Important CodeS ru c 919 8 NORMAL 5 919 8 xen lem PG 919 8 Page Date 28 February 2006 919 1 Section 919 mE Pilot s Operating Handbook BECKER 4401 Transponder XTRA EXTRA 300 Left blank intentionally 919 2 Page Date 28 February 2006 Pilot s Operating Handbook E Section 919 EXTRA 300 BECKER 4401 Transponder 919 1 GENERAL The Becker panel mounted ATC 4401 Transponder is 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 interrogation
17. 950 90 SL 171 561 527 1729 177 581 548 1798 185 607 586 1923 2095 2000 181 594 558 1831 188 617 580 1903 197 646 602 1975 4000 192 630 592 1942 199 653 615 2018 208 682 639 2096 6000 203 666 627 2057 211 692 652 2139 220 722 678 2224 870 85 SL 158 518 488 1601 164 538 507 1663 171 561 527 1729 1918 2000 165 541 518 1699 175 574 537 1762 181 594 558 1831 4000 177 581 548 1798 185 607 570 1870 192 630 592 1942 6000 188 617 582 1909 195 640 605 1985 203 666 627 2057 820 80 SL 150 492 465 1526 156 512 483 1585 163 535 502 1647 1809 2000 159 522 492 1614 166 545 511 1677 173 568 532 1745 4000 168 551 522 1713 176 577 543 1781 184 604 565 1854 6000 179 587 553 1814 186 610 575 1886 194 636 598 1962 5 14 Page Date 20 April 2002 Pilot s Operating Handbook XTR A EXTRA 300 Paragraph 6 1 6 2 6 2 1 6 3 6 3 1 6 3 2 6 4 6 5 6 6 SECTION 6 WEIGHT AND BALANCE AND EQUIPMENT LIST Table of Contents Page ee aea aea 6 3 AIRCRAFT WEIGHING PROCEDURE 6 3 Owners Weight And Balance Record eene 6 4 CENTER OF GRAVITY CALCULATION SAMPLE PROBLEM
18. Current Extreme Values are also shown on the LC Display and signed with an for example A 7 3g 3 59 903 6 Page Date 20 April 2002 Pilot s Operating Handbook Section 903 EXTRA 300 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 0g 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 A 004 and the Current Extreme Value is reset to 09 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 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 occured since the last reset of these values They are signed with a B as first character of a line like the following example B 84g B 4 2g In case you want to reset these two values you have to press S2 and the instrument sets the Total Extreme Values to 0g and returns into the Normal Operating Mode Provided you pushed 51
19. INFORMATION MANUAL EXTRA 300 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 Approved Pilot s Operating Handbook required for operation of the airplane Left blank intentionally Pilot s Operating Handbook EXTRA 300 MAIN TABLE OF CONTENTS Section Page 0 PUBLIGATION GUIDANGE een rae taeda tun ea uaa dd 0 1 Uc dn 1 1 2 LIMITATIONS tte et tnn ert rt aa a 2 1 3 EMERGENCY PROGEDUBES eit attt td ed nnde 3 1 4 NORMAL PROCEDURES ertt egent ctetur re er qae 4 1 b PERFORMANCE entree nU RR ERR ERA ERR Le uM 5 1 6 WEIGHT AND BALANCE AND EQUIPMENT LIST sss 6 1 7 DESCRIPTION AND OPERATION OF AIRCRAFT AND SYSTEMS 7 1 8 HANDLING SERVICING AND 8 1 9 SUPPLEMENTS eiit rtt rte tre rk uasa 9 1 Page Date 20 April 2002 XIRA Pilot s THIS HANDBOOK SHALL ALWAYS BE CARRIED ON BOARD DURING FLIGHT PILOTS OPERATING HANDBOOK PREPARED THIS
20. 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 THE UNIT PRE FLIGHT CHECK 1 Check that 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 28 February 2006 Pilot s Operating Handbook 2 Section 920 EXTRA 300 BECKER 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 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 Al or Flight Number FN is displayed in the bottom line Flight level
21. The default value for Al is the Tail Number of the aircraft and is stored in the Address Module If aflight plan exists it has to be checked which AI 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 on 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 28 February 2006 920 7 Section 920 Pilot s Operating Handbook BECKER ATC 6401 Transponder EXTRA 300 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 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 chara
22. 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 permanently 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 Value is shown in the lower line They are both signed by an as first character of every line The Current Extreme Val ues 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 00 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 th
23. 1 RPM control HIGH RPM Full forward 2 Throttle OPEN Take off power 3 Airspeed Minimum 90 KIAS 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 20 April 2002 4 9 Section 4 Pilot s Operating Handbook Normal Procedures 300 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 max 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 WARNING The high permissible load factors of the airplane 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
24. 5 10 Section 5 Performance Pilot s Operating Handbook EXTRA 300 RANGE AND ENDURANCE 5 8 SYH 6 2 009 005 007 0002 000 0009 0008 008 002 00001 0002 000v 00091 SNOLLIQNOO VSI SNISInHO OL H3MOd O L 18 SN 80 1v9 SN 99 1112 JAH3S3H WOSNEL O L 9 SN Ezr 091 land WLOL 581 5602 Dy 056 LHOI3M NOILIGNOD 1333 SHH 2 Sip 0008 9H S lZ 2dM OSEZ WdY 7S9 8 S 118 3511439 9 11135 uaMOd 0002 000 0009 0008 00001 00021 000 00091 1333 5 11 Page Date 20 April 2002 Section 5 Pilot s Operating Handbook Performance XTRA EXTRA 300 5 9 FUEL CONSUMPTION 5 9 FUEL CONSUMPTION LITER STANDARD DRY HOUR 23 8 90 214 80 18 5 70 15 9 60 13 2 50 10 6 40 7 9 30 5 3 20 2 6 10 GAL HOUR SL 2000 4000 6000 8000 10000 12000 14000 16000 ft PRESSURE ALT PA EXAMPLE PA 8000 ft ISA POWER SETTING 65 NM FUEL CONSUMPTION LITER gt 52 LTR HRS 13 7 GAL HRS gt 3 25 12 3 NM GAL 457 15 1 4 0 557 13 2 3 5 657
25. 7345 6380 907 7 DESCRIPTION OF THE SYSTEM Wing tank The leading edge section of each wing in front of main spars forms an integral fuel tank providing two interconnected 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 reason able time For max fuel capacity the first filled side have to be filled once again The wing tank can be completely emptied in flight 907 8 HANDLING SERVICING AND MAINTENANCE Not affected Page Date 20 April 2002 907 5 Section 907 IL Pilot s Operating Handbook Long Range Wing Tank Capacity 300 Left blank intentionally 907 6 Page Date 20 April 2002 Pilot s Operating Handbook XTR A EXTRA 300 Paragraph 908 1 908 2 908 3 908 4 908 5 908 6 908 7 908 8 SECTION 908 AIRTOW HOOK Table of Contents Page cj zl M 908 3 LIMITATIONS sme 908 3 EMERGENCY 5 e riter 908 4 NORMAL PROCEDURES cincuenta annuam nh anat n X
26. 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 VA Maneuvering speed VNE Never exceed speed VNO Maximum structural crusing speed VS Stalling speed or minimum steady flight speed VX 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 300 XTRA General Meteorological terminology ISA International standard atmospheric condition OAT Outside air temperature 1 10 SECONDARY TERMINOLOGY FPM Feet minute ft Feet 0 3048 m m Meter inch inch 2 54 cm L Liters Gal US gallon 3 79 liters Qts US quart 0 946 liters hp Horse power english h Hour kts Knots NM h 1 852 kilometer per hour Lbs English pound 0 4536 kg hPA hekto Pascal IN HG Inches of mercury MP Manifold pressure PA Pressure altitude ft NM Nautical miles 2 1 852 km RPM 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 Da
27. 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 triggered at the transponder 1 The IBIT Initiated Built in Test can be activated in any mode excluding the configuration mode with the push of F and G atthe same time The action starts with the leading edge ofthe second pushed button The IBIT works as follows in all
28. Clean the injector nozzle if required remove carbon debris 309 6 Page Date 20 September 200 mm XTRA E After each flight with activated Smoke System Clean the aircraft belly fairing and the rudder cable from oil slick NOTE The rudder cables might suffer from increased wear when they are covered with smoke oil and dust XTRA Piot s Operating Handboc Left blank intentionally Page Date 20 September 200 Pilot s Operating Handbook TR A EXTRA 300 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 912 7 LIMITATIONS jiet 912 8 EMERGENCY PROCEDURES 912 8 NORMAL PROCEDURE 912 8 azizell bee 912 8 Page Date 28 February 2006 912 1 Section 912 mE Pilot s Operating Handbook FILSER TRT 600 Transponder XTRA EXTRA 300 Left blank intentionally 912 2 Page Date 28 February 2006 Pilot s Operating Handbook E Section 912 EXTRA 300 XTRA
29. Steerable Tail Wheel eiie 4 p Electric Pedal Adjustment 1 4 p Electronic Accelerometer 10 p Emergency Locator Transmitter 8 p 6 p Digital RPM Indicator e crecen oec eer cnet eu niwan 6 p Long Range Wing Tank 6 p 2222222 2 1 8 p Smoke System 6 p aci e 0 p HeSerVed iudicandi ici 0 p FILSER TRT 600 Transponder 2 ence eire et encre ne aai 8 p FILSER TRT 800 8 p GARMIN GTX 327 6 p GARMIN GTX 330 Transponder eese esses seen nenne nnn nnns annt 8 p BENDIX KING KT 76A Trans
30. and red LEDs This 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 area 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 906 4 Page Date 20 April 2002 Pilot s Operating Handbook Section 906 EXTRA 300 XTRA Digital RPM Indicator 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 magneto systems Tachometer Magneto Between the left and right magneto ignition system alert indicators is a yellow RPM Syn chronization 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 This operation 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 fractiona
31. 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 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 ATC 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 28 February 2006 920 9 Section 920 p Pilot s Operating Handbook BECKER ATC 6401 Transponder XTRA EXTRA 300 920 1 9 VFR CODE ACTIVATION 1 Press the VFR push button J The preselected 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
32. 0 08 0 11 A 1 Oil Press Sensor Mediamate 387 100MM 0 12 0 04 A or 387 100KV 1 Stall Sensor EXTRA 73106 1 0 07 0 57 R 1 Stall Warning Horn EMAG EM S 110P 0 13 1 60 R 1 G Meter EXTRA DSA 12 0 37 1 73 1 G Meter Kollsman or Pioneer AN5745 0 40 1 73 O or Bendix 1 G Meter EZE Technologies DA 55 0 16 1 74 1 ELT and Antenna Pointer 3000 10 0 90 1 71 1 Turn amp Bank Ind United Instruments 9501 2 TSO C3b 0 55 1 67 1 Turn amp Bank Ind Castleberry C101 TSO C101T 0 55 1 67 Page Date 28 February 2006 6 11 Section 6 XTRA Pilot s Operating Handbook Weight and Balance and Equipment List EXTRA 300 QTY ITEM MANUFACT P N WEIGHT ARM MARK IF REQUIRED R KG m INSTALLED OPTIONAL O ALTERNAT A 1 Altimeter front United Instruments UI5934PD 3 A 134 0 60 0 82 1 Altimeter front TAI 10 04500 0 60 0 82 1 Altimeter front metric Winter 4110 0 33 0 84 1 Altimeter rear United Instruments UI5934PD 3 134 0 60 1 75 R 1 Altimeter rear TAI 10 04500 0 60 1 75 A 1 Altimeter rear metric Winter 4110 0 33 1 77 1 Altitude Encoder ACK A 30 0 15 1 50 1 Airspeed Ind front Winter 6533 321 0 21 0 82 1 Airsp Ind front metric Winter 6531 321 0 21 0 84 1 Airspeed Ind front United Instruments UI8030 B 835 0 22 0 82 1 Airspeed Ind rear Winter 6533 321 0 21 1 77 R 1 Airsp Ind rear metric Winter 6531 321 0 21 1 74 1 Airspeed Ind rear United
33. 11 4 3 0 9 5 2 5 oe 1 0 POWER SL 2000 4000 6000 8000 10000 12000 14000 16000 ft PRESSURE ALT PA 5 12 Page Date 20 April 2002 Pilot s Operating Handbook Section 5 EXTRA 300 XTRA Performance 5 10 CRUISE PERFORMANCE 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 cont Power climb to cruising altitude and a reserve of 21 liters 5 55 Gal for 45 minutes with 45 Power 2 liters 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 1 ft RPM INHG 96 Hp l h gal h Kts Kts h Best 2000 2400 25 1 75 225 68 7 18 2 167 6 160 1 91 320 Power 2200 24 2 65 195 50 5 13 3 159 3 152 2 60 413 2000 23 5 55 165 42 6 11 3 150 2 144 3 08 462 2000 20 2 45 135 36 5 9 6 139 9 134 3 59 502 4000 2400 24 6 75 225 68 7 18 2 170 9 158 1 91 324 2200 23 7 65 195 50 5 13 3 162 4 150 2 59 418 2000 23 0 55 165 42 6 11 3 153 1 142 3 06 467 2000 19 7 45 135 36 5 9 6 142 6 133 3 59 507 6000 2200 23 2 65 195 50 5 13 3 165 6 149 2 57 422 2000 22 5 55 165 42 6 11 3 156 1 141 3 04 472 2000 19 3 45 135 36 5 9 6 145 4 131 3 53
34. 15 Kts 15 kts 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 should be carried on board The pilot has to comply with Check list for daily check and inspections see Section 8 Handling Servicing and Maintenance Page Date 20 April 2002 4 3 Section 4 Bead Pilot s Operating Handbook Normal Procedures 300 4 1 PREFLIGHT INSPECTION 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 1 Pilot s Operating Handbook AVAILABLE 2 Airplane weight and balance CHECKED 3 Structural temperature CHECK STRUCTURAL OVERHEAT INDECATOR ON WING MAIN SPAR WEB FROM THE FRONT COCKPIT 4 Ignition switch OFF 5 Master switch ON 6 Fuel quantity indicators CHECK 7 Master switch OFF 8 Fuel shutoff valve ON 2 Empennage 1 All round inspection canopy surfaces CHECK stabilizer elevator trim rudder and tailwheel 2 Horizontal stabilizer attachment bolts CHECK FOR FREEPLAY BY MOVING THE TIP OF THE HORIZ STABILIZER UP AND DOWNWARDS 3 Right Wing 1 Aileron freedom of movement
35. 7 31 5 32 3 33 1 33 2 34 6 35 4 inch CENTER OF GRAVITY cm inch AFT OF REF DATUM Page Date 20 April 2002 6 9 Section 6 Weight and Balance and Equipment List XTRA Pilot s Operating Handbook EXTRA 300 6 6 EQUIPMENT LIST EA300 S N QTY ITEM MANUFACT P N WEIGHT ARM MARK IF REQUIRED R KG m INSTALLED OPTIONAL O ALTERNAT A 1 Engine Textron Lycoming AEIO 540 L1B5 194 90 0 72 R 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 A 1 Magnetos Bendix D6LN 3000 5 20 0 15 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 79 Silencer GO3 606500 1 Exhaust System Gomoizig 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 R 1 Single Oilcooler rear Niagara 20009A 1 81 0 22 A 1 Single Oilcooler rear Aero Classics 8000353 1 65 0 22 A 1 Set Fuel amp Sens div MS28741 with 6 30 0 21 R Hoses in Eng Comp firesleeve 1 Set Fuel amp Sens Parker Stratoflex PTFE Type 124J 4 90 0 2
36. Dual control cub type mounted on the left side in cockpit Page Date 28 February 2006 7 11 7 Pilot s Operating Handbook Description and Operation of Aircraft and Systems X TRA EXTRA 300 7 10 6 MIXTURE Vernier control located at left side of rear cockpit red knob 7 10 7 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 SHUTOFF VALVE Dual control A rotary fuel shut off is mounted behind the firewall A torque tube is mounted both cockpits at the right side and a 90 turn on the handle opens the valve Position left closed Position up open 7 10 9 EXHAUST SYSTEMS OPTIONAL Optionally the EA 300 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 root section of each wing in front of main spars forms an integral fuel tank providing two tanks each with 60 litres total 120 Ltr 31 7 US Gal The tanks can be compltely emptied in flight but the normal amount of unusable fuel is approximately 2 Liters 0 5 US Gallon Each wingtank has a 2 diameter filler cap for gravity refueling An acro tank 40 litres 10 6 US Gal is mounted in the fuselage j
37. February 2006 916 1 thru 916 6 28 February 2006 4 9 thru 4 12 20 April 2002 917 1 thru 917 8 28 February 2006 5 1 thru 5 14 20 April 2002 918 1 thru 918 6 28 February 2006 1 iU 6 2 utes 20 April 2002 919 1 thru 919 8 28 February 2006 6 uae ote 28 February 2006 920 1 thru 920 12 28 February 2006 Page Date 20 September 2006 Handbook SECTION 1 GENERAL Table of Contents Paragraph Page 1 0 DESCRIPTION srcu 1 3 1 1 55 ce EAA RR 1 3 1 2 MANUFACTURER 1 3 1 3 TECHNICAL DATA 1 3 1 3 1 SNOW DOWO 1 3 1 3 2 Mam Datel 1 4 1 3 3 ee ET 1 4 1 3 4 FIOM ZON TAN Tall T 1 4 1 3 5 mio adada 1 4 1 3 6 Tail 1 4 1 3 7 alles aa 1 4 1 4 a clle 1 5 1 5 2 1 5 1 5 1 Exhaust Systems
38. Ibs COPILOT FUEL IN FRONT WING 120 L SEAT 31 7 US Gal kg 008 Ibs Page Date 20 April 2002 EXTRA 300 Pilot s Operating Handbook XTRA Weight and Balance and Equipment List Section 6 9 62 942 0 06 0 cg 0 08 0 81 0 01 ALldMW3 OOL 11443 9 HLIM AINO 52110808028 008 v94l 182 I 0428 0 1 ssi 182 II 0828 0 1 006 59861 182 0 1 6605 sql 2 LH913M CWS 3144905 NOIEIZSJTOIBJ ALIAGHS 40 BHSILlNSJ 9 Page Date 20 April 2002 Pilot s Operating Handbook Section 6 EXTRA 300 XTRA Weight and Balance and Equipment List 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 40 L 28 8 kg 63 5 Ibs 120 Fuel In Wing Tanks 86 4 kg 190 5 Ibs Aircraft Empty Weight 654 0 kg 1442 Ibs 949 2 kg 2093 Ibs To find C G follow line Pilot Rear Seat from Empty Weight to 90 kg 198 5 Ibs Point 1 Continue on line Copilot Front Seat to 90 kg Point 7 Now follow line Fuel via Point 8 40 L 10 6 Gal Acro Fuel to Point 9 120 L 10 6 Gal Fuel in Wing Tank FIND Weight 949 kg 2093 Ibs C G 84 2 cm 33 1 inch 6 3 2 WEIGHT AND BALANCE RECORD SHEET WEIGHT MOMENT EMPTY WEIGHT
39. MANUAL IS FURNISHED TO BY THE CIVIL AVIATION AUTHORITIES AS A PART OF THE CERTIFICATION EXTRA Flugzeugproduktions und Vertriebs GmbH MATERIAL FOR THIS MODEL Page Date 28 February 2006 Pilot s Operating Handbook XTR A EXTRA 300 Paragraph SECTION 0 PUBLICATION GUIDANCE Table of Contents Page INTRODUCTION 0 3 5 0 3 WARNINGS CAUTIONS AND 0 4 LOG OF EFFECTIVE PAGES oui a Pc cornua dL ere 0 5 Page Date 20 April 2002 0 1 Section 0 Pilot s Operating Handbook Publication Guidance EXTRA 300 Left blank intentionally 0 2 Page Date 20 April 2002 Pilot s Operating Handbook Section 0 EXTRA 300 Publication Guidance 1 INTRODUCTION This handbook contains 10 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 2 NOTES 2 1 This Flight Manual applies only to the aircraft whose nationality and registration marks are noted on the title page 2 2 It is the responsibility of the pilot to be familiar with the contents of this Flight Manual including revisions and any relevant supplements 2 3 Pages of this Airplane Flight Manual must not be exch
40. Psi 90 Psi yellow arc 90 Psi 100 Psi red line 100 Psi OIL TEMPERATURE INDICATOR yellow arc lt 140 F green arc 140 F 210 F yellow arc 210 F 245 F red line 245 F CYLINDERHEAD TEMPERATURE INDICATOR yellow arc lt 150 F green arc 150 F 435 F yellow arc 435 F 500 F red line 500 F RPM INDICATOR green arc 700 RPM 2400 RPM yellow arc 2400 RPM 2700 RPM red line 2700 RPM METER green arc 5g 89 yellow arc 89 109 red line 109 FUEL FLOW INDICATOR green arc red radial Ogal h 35gal h 35 gal h 2 12 Page Date 20 April 2002 Pilot s Operating Handbook Section 2 EXTRA 300 XTRA Limitations MANIFOLD PRESSURE INDICATOR green arc 10 Hg 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 1 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 contr
41. Rpm 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 headwind the takeoff T O distance can be decreased by 5 For every 2kts tailwind up to 10 kts the T O distance is increased by 10 CAUTION All values are valid for single pilot air towing operation 820kg 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 Takeoff weight glider 350 Kg altitude T O 50 ft T O 50 ft T O 50 ft T O 50 ft T O 50 ft T O 1508 0 ft 2000 ft 4000 ft 6000 ft 8000 ft Takeoff weight glider 600 Kg Press 100 OAT altitude T O 50 ft 0 50 ft T O 50 ft T O 50 ft T O 50 ft T O 50ft 0 ft 2000 ft 4000 ft 6000 ft 8000 ft Takeoff weight 765 Kg Press 108 oc 200 altitude T O 50 ft T O 50 ft T O 50 ft T O 50 ft T O 50 ft T O 50 ft 0 ft 2000 ft 4000 ft 6000 ft 8000 ft Page Date 20 April 2002 908 5 Section 908 2 Pilot s Operating Handbook Airtow Hook 300 CLIMBRATE Conditions Power 2500 Rpm and full throttle mixture rich Speed of the aircraf
42. Systems X TRA EXTRA 300 7 10 POWER PLANT 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 antivibration counterweights The following accessories are included in the power plant installation Fuel Injector Bendix Magnetos Slick Alternator Electrosystems Starter B amp C Fuel pump Gates Lear Shielded ignition system Propeller governor drive Transistor voltage regulator Overvoltage relay The engine is operated with the following manual controls Throttle control dual RPM control Fuel mixture control The propeller governor monitors the RPM automatically and prevents overspeeding In the event that oil pressure is lost the propeller is automatically adjusted to coarse pitch in order to avoid overspeeding The use of 100 130 aviation grade fuel AVGAS 100 is the minimum grade recommended by the manufacturer of the AEIO 540 L1B5 D engine For continuous operation 115 145 aviation fuel is the maximum grade 7 10 Page Date 28 February 2006 Pilot s Operating Handbook mE Section 7
43. THIS AIRPLANE IS CERTIFICATED FOR VFR DAY OPERATION OPERATION IN KNOWN ICING CONDITIONS IS PROHIBITED on the rear instrument panel FUEL near the filler cap on each wingtank AVGAS 100 100 LL on the seperate hatch upper cowling FUEL SHUTOFF VALVE in both cockpits at the right side NOSE DOWN lt NEUTRAL gt NOSE UP near the handle at the right side TRIM in the rear cockpit WING TANK on the rear insrument panel under MUST BE EMPTY FOR ACROBATICS fuel capacity indicator USABLE FUEL 120 L 31 7 US GAL ACRO TANK INDICATION ON GROUND SHOWS FULL AT 38 L 10 US GAL AND ZERO 101 2 6 US GAL Page Date 20 April 2002 Section 2 Pilot s Operating Handbook Limitations XTRA EXTRA 300 ACRO TANK on the rear instrument panel under USABLE 38 L 10 US GAL fuel capacity indicator ACROBATIC 10 G 1 PILOT 8 9 2 PERSON ON BOARD MTOW 820 KG 1808 LBS MTOW 870 KG 1918 LBS NORMAL 6 G 3 G MTOW 950 KG 2095 LBS in both cockpits ACROBATICS INCL SPIN APPROVED PNUD NSO al near pump switch on the instrument panel in the rear cockpit ON OFF USE OF HEADSET IS REQUIRED onthe right side of both USE OF PARACHUTE IS RECOMMENDED instrument panels MAGNETIC near Mag Dir Indicator DIRECTION INDICATOR CALIBRATION LOW RPM lt PROP gt HIGH RPM on RPM control
44. are in the ON position the smoke system is not energized and will not run The smoke oil tank is filled by a refill pump through a quick connector located in the aircraft belly fairing A filled smoke oil tank is detected by a float switch placed in the 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 smoke oil tank through a solenoid valve and the injector nozzle into the hot exhaust gas to generate smoke The system consists of Floptube smoke oil tank with float switch Refill pump in the pilot compartment with quick connector in the belly fairing Injection pump in the engine compartment with a shut off solenoid in the pilot compartment ON OFF 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 OFF LY MEE 00000 SMOKE CONTROL GO BREAKER 909 8 HANDLING SERVICING AND MAINTENANCE At every refilling Check automatic shut off Additionally during the 100h Check Check the system for leakage lines fittings tank Check the smoke oil tank for proper attachment Check the function of the solenoid valve
45. cockpit potential green house effect a reversible temperature indicator STRUCTURAL OVERHEAT INDICATOR is applied on the rear web of the wing main spar in the carry through section After reaching the temperature limit of 72 161 6 F the word RISK appears and flying is prohibited STRUCTURAL CAUTION OVERHEAT While p word 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 2 14 4 AIRCRAFT IDENTITY PLACARD MANUFACTURER 9 EXTRA o EXTRA FLUGZEUGBAU GmbH FLUGZEUGPRODUKTIONS MODEL EA 300 UND VERTRIEBS GMBH SERIAL NUMBER MODEL EA 300 oTC NUMBER o SERIAL NUMBER O TC NUMBER A67EU 2 8 Page Date 20 September 2006 Pilot s Operating Handbook Section 2 EXTRA 300 XTRA Limitations 2142 OPERATING PLACARDS V 158 Kts Acro near airspeed indicator V 140 Kts Normal THE MARKINGS AND PLACARDS INSTALLED IN 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
46. considered For the prevention of a fire alarm inform the flight control before you activate the smoke system 5 Recommended Manifold pressure min 20 Hg 6 The activation of the smoke system on ground is only allowable for a brief system test 7 The operation of the smoke system is not allowable for the standard exhaust 6 into 2 PC 63104 with mounted external silencer NSD GO3 606500 8 Wearing a parachute is strongly recommended Operating Markings amp Placards SMOKE OIL External Next to the quick Cin cities CECENE ale HORE IG He e n seed f 40cts 551 9 2 USG eM ie throttle ever above control switch row OFF SMOKE iment panel BREAKER 2 circuit breaker row EMERGENCY PROCEDURES FAILURE OF THE SMOKE SYSTEM 1 Switch SMOKE ARM and SMOKE REFILL OFF 2 Circuit breaker PULL 5 Operating Handbook EXTRA 300 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 3 Fuel shutoff valve 4 Master switch 5 Airspeed IDLE CUT OFF OFF OFF 100 KIAS find your airspeed attitude that will keep the fire away from the cockpit 6 Land AS SOON AS POSSIBLE 7 If fire persists or aircraft is uncontrollable and wearing a parachute BAIL OUT SMOKE IN THE COCKPIT 1 Switch SMOKE ARM OFF 2 B
47. 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 G turn rotary encoder B until CFG appears in the bottom row ofthe 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 28 February 2006
48. 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 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 915 4 Page Date 28 February 2006 Pilot s Operating Handbook 2 Section 915 EXTRA 300 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 seco
49. identification codes 917 4 NORMAL PROCEDURES Not applicable 917 5 PERFORMANCE Not applicable Page Date 28 February 2006 917 7 Section 917 mE Pilot s Operating Handbook BENDIX KING KT 76A Transponder XTRA EXTRA 300 Left blank intentionally 917 8 Page Date 28 February 2006 Pilot s Operating Handbook TR A EXTRA 300 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 oot o 918 3 918 4 Squawk selection 918 4 Mod 918 5 Mode and C 918 5 LIMITATIONS e 918 5 EMERGENCY PROCEDURES cec rire reote cei utere 918 5 Important TE 918 5 5 2 aaa aanaeio 918 6 anaa eae donuts 918 6 Page Date 28 February 2006 918 1 Section 918 mE Pilot s Operating Handbook BECKER 2000 Transponder XTRA EXTRA 300 Left blank intentionally 918
50. 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 works 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 300 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 m 5 3 Performance Charts tee eco rendue euet axe re reget eas rat aai 5 3 Definition or 5 3 5 3 ISA CONVERSION
51. in acro tank 2 4 2 ENGINE LIMITATIONS a Tachometer gauge Max Take Off max 5 min 2700 RPM Max Continuous 2400 RPM NOTE If not stated somewhere else refer to Section 4 12 Acrobatic Maneuvers the aircraft may be operated in the acrobatic maneuvers up to 2700 RPM b Oil temperature gauge Max 24 9 Oil capacity Maximum sump capacity 16 qts Minimum sump capacity 12 qts Normal 9 pressure Minimum Idling 25 Psi Normal 55 95 Psi Starting Warm up Taxi and Take Off 115 Psi CAUTION It is normal for the oil pressure to flicker from 10 to 30 psi 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 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 40 Psi Min 18 Psi Min Idle 12 Psi 2 4 Page Date 28 February 2006 Pilot s Operating Handbook Section 2 EXTRA 300 XTRA Limitations f Cylinder head temperature Max 500 F 2 5 PROPELLER MT Propeller Entwicklung GmbH Federal Republic of Germany a Type MTV 14 B C C190 17 b Type 9
52. 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 flashing 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 long
53. 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 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 or 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 BIT after switching on During the PBIT any action from other switches are not accepted 920 6 Page Date 28 February 2006 Pilot s Operating Handbook 2 Section 920 EXTRA 300 XTRA BECKER 6401 Transponder During the PBIT the in the SBY mode butthis is notindicated on the display The operating mode indication on the display starts immediately after finalisation of the PBIT Negative results are indicated on the display with FAILURE The transpondermay be not switched into ON or ALT mode if any
54. of fire or explosion in aircraft Temperature extremes in aircraft d 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 E 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 high 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
55. s Operating Handbook Section 6 EXTRA 300 Weight and Balance and Equipment List QTY ITEM MANUFACT P N WEIGHT ARM MARK IF REQUIRED R KG m INSTALLED OPTIONAL O ALTERNAT A 1 Batt Charger Plug EXTRA 146 19 20 0 02 0 95 1 External 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 76 R 1 Ignition TCM 10 357200 1 0 15 1 76 R Switch 2 Wheel Cleveland 40 151 4 00 0 41 R 2 Main Wheel Tires Div 5 00 5 3 90 0 41 R 1 Tail Wheel 5 EXTRA 53200 5 50 5 73 R 1 Tail Wheel 5 EXTRA steerable 5 50 5 73 A 1 Tail Wheel 6 Assy Special Products 5 90 5 73 A Soft Aviation Inc 2 Brake Assy Cleveland 30 164 1 40 0 41 R 2 Brake Oyl front Cleveland 10 20 or 10 20E 0 55 0 40 R 2 Brake Oyl front Matco MC 4E 0 55 0 40 A 2 Brake Oyl rear Cleveland 10 20 or 10 20E 0 55 1 40 R 2 Brake Oyl rear Matco MC 4E 0 55 1 40 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 Seat rear Standard EXTRA 73201 4 2 70 2 46 R 1 Seat rear CFK EXTRA 83403 10 11 2 60 2 46 A 1 Seat front Standard EXTRA 73201 3 2 60 1 39 R 1 Seat front CFK EXTRA 83404 1 2 50 1 39 A 1
56. terrain and obstructions then reaching a safe altitude and airspeed 4 Master switch OFF 5 Touchdown SLIGHTLY TAIL LOW 6 Ignition switch OFF 7 Mixture IDLE CUT OFF 8 Fuel shutoff valve OFF 9 Brakes APPLY HEAVILY Page Date 28 February 2006 3 5 Section 3 Emergency Procedures XTRA Pilot s Operating Handbook EXTRA 300 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 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 OFF OFF INSPECT Page Date 20 April 2002 Pilot s Operating Handbook mE Section 3 EXTRA 300 XTRA Emergency Procedures 3 4 3 ENGINE FIRE IN FLIGHT 1 Mixture IDLE CUT OFF 2 Fuel shutoff valve OFF 3 Master switch OFF 4 Airspeed 100 KIAS find your airspeed attitude will keep the fire away from the cockpit 5 Land as soon as possible 3 5 ICING 3 5 1 INADVERTENT I
57. 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 itself 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 damped by anti shimmy connector springs Page Date 20 April 2002 901 3 Section 901 Pilot s Operating Handbook Steerable Tail Wheel XTRA EXTRA 300 901 8 HANDLING SERVICING AND MAINTENANCE During 50 hour inspection the bearing steelsleeve has to be lubricated on the point of lub
58. unit in the rear cockpit LEAN lt MIXTURE gt RICH on mixture control unit in the rear cockpit CLOSE lt THROTTLE gt OPEN near throttle control in both cockpits LOCK lt gt UNLOCK near canopy locking handles of each cockpit near the eyeball type adjustable vents 2 10 Page Date 28 February 2006 Pilot s Operating Handbook Z Section 2 EXTRA 300 XTRA Limitations APPROVED ACROBATIC MANEUVERS AND RECOMMENDED ENTRY AIRSPEEDS MANEUVERS SPEEDS min KIAS max KIAS Segment horizontal Line Vs 45 climbing 80 90 up 45 diving 90 diving 1 4 Loop climb Looping Stall turn Aileron roll Snap roll Tail slide Spin Inverted spin Inverted flight Less than 4 min Knife edge Less than 10 s CAUTION Particular caution must be exercised when performing maneuvers at speeds above Va 158 KIAS Large or abrupt control inputs above this speed may impose unacceptably high loads which exceed structural capability of the aircraft in both cockpits WARNING SOLO FLYING FROM on front instrument panel REAR SEAT ONLY Page Date 28 February 2006 2 11 Pilot s Operating Handbook EXTRA 300 X TR A 2143 INSTRUMENT MARKINGS AIRSPEED INDICATOR green arc 60 Kts 158 Kts yellow arc 158Kts 220 Kts red line 220 Kts OIL PRESSURE INDICATOR red line 25 Psi yellow arc 25Psi 55 Psi green arc 55
59. wing tank on the EA 300 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 194L 51 2 US Gallons Wingtanks 154 L 2 x 77 L 40 6 US Gallons Acro Center Tank 40 L 10 5 US Gallons Usable fuel capacity in the system 192 L 50 7 US Gallons For acrobatic flight wing tanks must be empty Usable fuel capacity for acrobatic 38 L 10 0 US Gallons WEIGHT LIMITS Max allowed empty weight Normal category 724 kg 1596lbs PLACARD The existing WINK placard has to be replaced by the following placard WING TANK in the rear instrument panel MUST BE EMPTY FOR ACROBATICS USABLE FUEL 154L 40 6 US GAL digali EMERGENCY PROCEDURES Not affected NORMAL PROCEDURES Not affected Page Date 20 April 2002 907 3 Section 907 2 Pilot s Operating Handbook Long Range Wing Tank Capacity 300 907 5 PERFORMANCE RANGE AND ENDURACE 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 litre 5 5 US Gal for 45 minutes with 45 Power 2 0 litres 0 53 US Gal unusable fuel is taken into accoun
60. 00 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 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 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 display LOW POWER SUPPLY If the power supply to the transponder drops below 10 Volts the flag BAT 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 an authorized se
61. 1 A Hoses in Eng Comp Aeroquip or AE466 1 Set Fuel amp Sens Parker Stratoflex PTFE Type 124J 3 70 0 15 A Hoses in Eng Comp Aeroquip or AE466 single Oil Cooler Sys 1 Set Fuel Hoses div MS28741 1 37 0 30 R in Cabin Comp 1 Set Fuel Hoses Parker Stratoflex PTFE Type 124 0 91 0 30 A in Cabin Comp or Aeroquip or 666 1 Sens Hoses Cabin Knapp Hoerbiger HS3MA OR H3MM 0 30 0 87 R Cil Fuel amp MA Press 1 RPM Vernier Control ACS Products Co A 750 30 1200 0 71 0 55 R 1 Mixture Vernier Control ACS Products A 750 20 1080 0 65 0 70 R 1 Throttle Control Teleflex Marine F303 02000 0 45 0 01 R 1 Propeller MT Propeller MTV 9 B C C200 15 30 40 1 15 R 1 Spinner MT Propeller P 208 B R 1 Spinner MT Propeller P 810 2 A 1 Propeller MT Propeller 14 190 17 29 80 1 15 1 Spinner MT Propeller P 238 A 1 Spinner MT Propeller P 967 A 1 Cowling GRP incl EXTRA 23205 01 amp 02 9 80 0 52 R Air Intake Screen EXTRA 83802 1 1 Cowling CRP incl EXTRA 23205 301 amp 302 8 80 0 52 A Air Intake Screen EXTRA 83802 1 1 Cowling incl EXTRA 83001 0 9 20 0 53 A Air Intake Screen 6 10 Page Date 28 February 2006 Pilot s Operating Handbook Section 6 EXTRA 300 Weight and Balance and Equipment List QTY ITEM MANUFACT P N WEIGHT MARK IF REQUIRED R KG m INSTALLED OPTIONAL O ALTERNAT A 1 Governor Woodward X
62. 1138 Page Date 20 April 2002 Section 5 Pilot s Operating Handbook EXTRA 300 RATE CLIMB PERFORMANCE 5 6 3968 581 J81 496 591 991 921 7 81 9861 S602 JOZ 301 201 30z 6 1H9I3M 0524 008 058 006 0 lt 6 USI USI USI USI 00 2 0082 002 uru 1j 4 89 1300091 3200081 498 1300021 95 3300001 e 140009 30009 30007 30002 15 m Cc gt 11 091 OSES n vsi 0008 YSI 0002 481 098 LHOI3M 3l1dWVX3 SNONNILNOOD HLIM 31V8 1539 95 Ol Zl Vi 5 204 Page Date 20 April 2002 Pilot s Operating Handbook Section 5 EXTRA 300 XTRA Performance TIME TO CLIMB FUEL TO CLIMB 5 7 1 9 5 186 977 076 691 0 597 608 9861 220281 91 vei 2101 8 9 056 006 OL TANA 120 SN 911 np gv gWrmo OL 1909 gWr19 OL VSI 0008 lt YSI 0002 11 S81 481 098 18 921 vS9L 058 008 OSL 00 4 VSI d33dS LV H3MOd LNOO 02 SNOILIGNOOD gWI 13 01 AWIL OL IANA EWI 193 01 AWIL 4 S Page Date 20 April 2002
63. 14 4 LIMITATIONS 222 914 5 EMERGENCY PROCEDURES gt 914 6 CodeS E 914 6 5 1 914 6 PERFORMANCE 914 6 Page Date 28 February 2006 914 1 Section 914 Pilot s Operating Handbook GARMIN GTX 327Transponder EXTRA 300 Left blank intentionally 914 2 Page Date 28 February 2006 Pilot s Operating Handbook Posuit Section 914 EXTRA 300 GARMIN GTX 327 Transponder 914 1 GENERAL The GARMIN GTX 327 is a panel mounted TSO d transponder with the addition of timing functions The transponder is 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 The GTX 327 owner accepts all responsibility for obtaining the proper license before using the transponder The coverage you can 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 sho
64. 2 Page Date 28 February 2006 Pilot s Operating Handbook 2 Section 918 EXTRA 300 BECKER 2000 Transponder 918 1 GENERAL The Becker panel mounted ATC 2000 Transponder is 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 acoded response of pulses to ground based radar ona 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 digit B Third digit Fourth digit D M 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 one 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 o
65. 210988 1 10 0 91 R or A 210988 1 Governor MT Propeller P 880 5 1 10 0 91 A 7 Switches Cutler Hammer div 0 28 1 76 R 7 Switches Kissling div 0 28 1 76 A 11 Circuit Breaker Potter amp Brumfield div 0 50 1 75 R 11 Circuit Breaker ETA or Klixon div 0 30 1 75 A 1 Main Bus Fuseholder MTA 03 00360 0 03 0 02 1 Main Bus Strip 02 00300 40 1 PCB Auto Fuse EXTRA 83290 1 0 01 0 03 1 Fuel Cont Probe VDO 226 801 015 001 G 0 12 0 50 R Wing Tank 1 Fuel Cont Probe VDO 224 082 008 021R 0 20 0 55 R Header Tank 1 Fuel Cont Ind VDO 301 271 036 001 K 0 08 1 75 R Wing Tank or 301 030 001 G 1 Fuel Cont Ind VDO 301 272 052 001 K 0 14 1 75 R Header Tank or 301 030 002 G 1 Ammeter VDO 190 004 039 002 0 08 1 75 R or 190 037 002 G 1 Volt Ammeter Electronics Intern VA 1A 0 26 1 75 A 1 Shunt Electronics Intern S 50 0 09 1 65 A 1 Volt Ammeter Electronics Intern VA 1A 50 0 22 1 75 A 1 RPM Indicator VDO 333 230 115 002 0 31 1 73 R or 333 035 001 G 1 RPM Indicator digital Horizon P100 230 643 00 0 68 1 73 1 Magn Dir Ind Airpath C 2300 0 25 1 75 1 Oil Press AMITEK or Christen 61943 0 51 1 75 Oil Temp Ind 1 Oil Press Westach 3DA3 3MM 0 14 1 75 A Oil Temp Ind 3 1 8 or 3DA3 3KV 1 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 75 A Oil Temp Ind 2 1 4 or 2DA3 3KV 1 Oil Temp Sender Westach W399 S9
66. 3 2 3 ENGINE FAILURE DURING FLIGHT RESTART PROCESS 1 Airspeed 80 KIAS 2 Fuel shutoff valve ON 3 Mixture RICH 4 Boost pump ON 5 Ignition switch BOTH or START if propeller has stopped 3 4 Page Date 20 April 2002 Pilot s Operating Handbook mE Section 3 XTRA Emergency Procedures EXTRA 300 3 2 4 3 2 5 3 3 3 3 1 3 3 2 OIL SYSTEM MALFUNCTION If oil pressure indicates low Apply positive g If oil pressure is not regained than 1 Airspeed 80 KIAS 2 Throttle REDUCE TO IDLE 3 Engine oil temperature OBSERVE INDICATION 4 Land ASAP WARNING If oil pressure drops to 0 psi the propeller pitch changes automatically to coarse high pitch with a corresponding decrease in RPM ALTERNATOR FAILURE An alternator failure is indicated by the red light of the low voltage monitor If red light illuminates 1 Alternator SWITCH OFF AND ON 2 Low voltage monitor CHECK INDICATION 3 Red light off CONTINUE FLIGHT If red light illuminates again 4 Land AS SOON AS PRACTICAL FORCED LANDINGS EMERGENCY LANDING WITHOUT ENGINE POWER 1 Seat belts shoulder harnesses SECURE 2 Airspeed 80 KIAS 3 Mixture IDLE CUT OFF 4 Fuel shutoff valve OFF 5 Ignition switch OFF 6 Master switch OFF 7 Touchdown SLIGHTLY TAIL LOW 8 Brakes OPTIMUM BRAKING PRECAUTIONARY LANDING WITH ENGINE POWER 1 Seat belts shoulder harnesses SECURE 2 Airspeed 80 KIAS 3 Selected field FLY OVER noting
67. 512 Economy 8000 2350 21 5 65 195 52 0 13 7 169 0 147 2 49 415 Economy 2050 21 4 55 165 43 0 11 4 159 3 139 2 99 472 Economy 2000 18 8 45 135 36 5 9 6 148 4 130 3 51 517 Economy 10000 2150 19 9 55 165 43 7 11 5 162 5 138 2 93 469 2000 18 4 45 135 36 5 9 6 151 4 129 3 48 522 12000 2300 18 3 55 165 45 2 11 9 165 9 136 2 81 458 Economy 2000 17 9 45 135 36 5 9 6 154 5 127 3 44 526 Economy 14000 2075 17 7 45 135 37 1 9 8 157 8 122 3 36 520 Economy NOTE 1 For temperatures above below Standard ISA increase decrease Range 1 7 Endurance 1 196 for each 10 C above below Standard Day Temperature for particular 2 Best Power or Best Economy see latest issue of Textron Lycoming altitude Manual 4 10 Series AEIO 540 Operator s Page Date 20 April 2002 5 13 Section 5 Pilot s Operating Handbook Performance EXTRA 300 5 11 LANDING PERFORMANCE Power Idle Runway Concrete Brakes maximum NOTE For every knot headwind the landing distance can be decreased by 3 On a solid dry and plain Grass Runway the landing is increased by 15 OAT 0 C 32 F 15 C 59 F 30 C 86 F Landing Airspeed Land Land Land Land Land Land weight Roll over Roll over Roll over 50 ft 50 ft 50 ft kg KIAS ft m ft m ft m ft m ft m ft m ft Ibs
68. 6 riae nnnc ccnseeecnentadenaneccenncdseaneesqacivaureusunented 901 3 901 7 DESCRIPTION OF THE SYSTEM 901 3 901 8 HANDLING SERVICING AND MAINTENANCE 901 4 Page Date 20 April 2002 901 1 Section 901 Pilot s Operating Handbook Steerable Tail Wheel EXTRA 300 Left blank intentionally 901 2 Page Date 20 April 2002 Pilot s Operating Handbook 55 Section 901 XTRA Steerable Tail Wheel EXTRA 300 901 901 1 901 2 901 3 901 4 901 5 901 6 901 7 STEERABLE TAIL WHEEL GENERAL To improve taxi and handling quality the EXTRA 300 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 LIMITATIONS 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
69. 6 Page Date 20 April 2002 Pilot s Operating Handbook Section 904 EXTRA 300 XTRA 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 OFF used to deactivate transmitter or to insure non activation by M handling 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 G switch only OFF used to deactivate transmitter after automatic 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 for
70. 6A 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 a continuos report of your altitude which are automatically updated in 100 foot increments NOTE The KT 76A owner accepts all responsibility for obtaining the proper license before using the transponder Function Selector Reply Light Code Windows KT76A BENDIX KING Ident Pushbutton Control Knobs 916 1 1 CODE SELECTION 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 code There is no need to move the caret back to the first digit it will automatically return after about five seconds The KT 76A will retain the reply code through power shutdowns if the code has not been changed during the 5 seconds prior to removing power 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 28 February 2006 916 3 Section 916 Pilot s Operating Handbook BENDIX KING KT 76A Transponder 300
71. 7 Descriptions and Operation 8 6 GROUND HANDLING a Due to its low weight and the free swiveling tail wheel two persons can easily move the airplane by hand b To tie down the airplane M6 nut plates are provided in the wing tips where ring bolts can be screwed in The tail wheel leg can be used as third point to tie down the airplane If the aircraft is parked in the open it must be protected against the effects of weather the degree of protection depending on severity of the weather conditions and the expected duration of the parking period When the airplane is parked in good weather conditions for less than a half day park the aircraft headed into the wind and place wheel chocks at the main wheels To level the aircraft the tail wheel is rested a balance and jacked to a position that the fuselage reference line upper fuselage stringer tube is horizontal There are two engine hoists provided on the top of the engine which can be used to lift the airplane with a crane Tail wheel resting on ground 8 4 Page Date 20 April 2002 Pilot s Operating Handbook XTRA EXTRA 300 Section 9 901 902 903 904 905 906 907 908 909 910 911 912 913 914 915 916 917 918 919 920 SECTION 9 SUPPLEMENTS Doc No EA 03701 1 Table of Contents Pages EIPITIuaCcME 4 p
72. 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 inthe 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 Lightindicates 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 the KT 76A Switching the function selector to the TST position a series of internal tests is performed to check the KT 76A 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 28 February 2006 Pilot s Operating Handbook 2 Section 916 EXTRA 300 XTRA BENDIX KING KT
73. 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 in Mode or normal mode To operate in Mode 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 28 February 2006 916 5 Section 916 mE Pilot s Operating Handbook BENDIX KING KT 76A Transponder XTRA EXTRA 300 Left blank intentionally 916 6 Page Date 28 February 2006 2 Handbook XTR A SECTION 917 BENDIX KING KT 73 TRANSPONDER Table of Contents Paragraph Page 917 1 GENERAL c PERENNE 917 3 917 1a FUNCTION MOD te 917 4 917 16 Gode Selecti M 917 4 917 1c Buttons selectors for other KT 73 917 5 917 1d Funcion DIoplay EE 917 6 917 Programming MOoGOe iet eu tes aee Ur uve rre 917 6 917 1f
74. ASE 3 Landing PERFORM AS PRACTICAL D TOW BREAK 1 Pilot of the glider INFORM 2 Landing PERFORM AS PRACTICAL 908 4 NORMAL PROCEDURES Preflight inspection starting procedures take off procedure and the following climbing flight have to be carry out in accordance with Chapter 4 Normal Procedures 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 tightened 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 steep 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 908 4 Page Date 20 April 2002 Pilot s Operating Handbook Section 908 EXTRA 300 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 in Meter Conditions Power over 2600
75. CEDURES 5 2 o en cian e fes 4 8 4 8 1 Bre 4 8 4 8 2 4 8 4 8 3 Balore 4 8 4 8 4 E 4 8 4 9 GO AROUN D m 4 9 410 PESE 4 9 4 11 LEAVING THE AIRGRAFT ge H 4 9 4 12 ACROBATIC MANEUVERS 4 10 4 12 1 VEINTE NU Um NU A A 4 10 4 12 2 5 RR 4 10 4 12 3 A 4 12 Page Date 28 February 2006 4 1 4 Pilot s Operating Handbook Normal Procedures 300 blank intentionally 4 2 Page Date 20 April 2002 Pilot s Operating Handbook Section 4 EXTRA 300 p X TRA Normal Procedures SECTION 4 NORMAL PROCEDURES 4 0 GENERAL 4 0 1 AIRSPEEDS FOR NORMAL OPERATION SPEEDS IN KIAS CATEGORY ACRO NORMAL 1 seat 2 seats Start Rotating Speed 60 62 65 Climb VX 87 89 93 Vy 96 99 104 Recommended Normal Climb Speed 100 105 110 Max Cruise 185 185 185 Landing Approach 80 85 90 on Final 72 74 78 Go Around Speed 90 95 100 Recommended Airspeed For Flight In Rough Air maximum VA 158 VA 158 VA 140 Max Demonstrated Cross Wind Component 15 Kts
76. CING 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 Kts if possible Pull mixture to lean Open canopy the lowpressure over the canopy in normal flight will flip the canopy full open immediately Take off headset Open seat belt Leave airplane to the left side Try to avoid wing and tail Open parachute Page Date 28 February 2006 3 7 Section 3 Pilot s Operating Handbook Emergency Procedures 300 3 8 EMERGENCY EXIT AFTER TURN OVER 1 Master switch OFF 2 Fuel shutoff valve OFF 3 Seat belts OPEN 4 Parachute harnesses 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 can 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 land
77. CTION 3 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 the aircrew from taking any additional action necessary to deal with the emergency The procedures contain items classified as critical or noncritical The critical items are actions that shall be performed immediately to avoid aggravating the emergency 3 0 2 GENERAL BEHAVIOUR IN EMERGENCY 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 tak
78. ERS 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 listed 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 300 Recommended entry Maneuvers speeds Symbol Remarks min KIAS max KIAS Segment horizontal Line V Vie e 45 climbing 80 V Pd 90 158 Vie 45 diving V Vas reduce throttle 90 diving V Vie reduce throttle 1 4 Loop climb 100 190 m Looping 100 190 DOE Stall turn 100 190 x Aileron roll 80 158 X full deflection Snap roll 80 140 HH tail slide 100 190 Spin V p Inverted spin V Knife edge 2150 e e 10s Inverted Flight gt V 190 E lt 4 min CAUTION Particular caution must be exercised when performing maneuvers at speeds above Va 158 KIAS Large or abrupt control inputs above this speed may impose unacceptably high loads whi
79. EXTRA 300 X TRA Description and Operation of Aircraft and Systems 7 10 2 OIL SYSTEM The oil is cooled by a Two Cooler System mounted on the left hand side in the engine compartment Alternatively a Single Cooler System is available In this case the oil is cooled by one oil cooler mounted on the aft right hand side of the engine The oil level is determined by a dip stick A thermostatic valve is fitted upstream of the oil cooler This valve ensures a quick warm up of the oil after engine start Oil capacity and grades Oil Max sump capacity 16 Min sump capacity Acrobatic 12 gts Normal 9 gts 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
80. FF 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 Kt headwind RATE OF CLIMB Fig 5 6 shows the Rate Of Climb using Take off Power The Rate of Climb at 2000 ft 2320 ft min The Time to Climb from 2000 ft to 8000 ft is acc to Fig 5 7 gt 4 0 0 9 min 3 1 min The Fuel to Climb from 2000 ft to 8000 ft 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 and a Power Setting of 65 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 45 Power 2 liters 0 53 US Gal unusable fuel is taken into account For the sample problem appr Total Fuel 160L 42 27 US Gal Warm Up amp T O 5L 1 32 US Gal Reserve 21L 5 55 US Gal Unusable Fuel 2L 0 53 US Gal Usable Fuel 1321 34 9 US Gal Range 415 NM 768 km Endurance 2 49 HRS 5 4 Page Date 20 A
81. 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 Knob for 1000 Rotating knot for 1 Sguitter flag elimina Code Test Monitor Eatery flag t Displ ay Flight Level a In Flight flag Standby Code Rotating knob for 10 Rotating knob IDENT for 100 Made Select a 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 28 February 2006 912 3 Section 912 p Pilot s Operating Handbook FILSER TRT 600 Transponder 300 ROTATING KNOBS Four rotating knobs are used to select the IDENT CODE The assignments X indicate the position of the code number set by each knob PUSH BUT
82. Flight Time which is controlled by the START STOP key COUNT UP Controlled by the START STOP and CLR keys COUNT DOWN Controlled by START STOP CLR and CRSR keys The initial Count Down time is entered with the 0 9 keys 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 LIMITATIONS Not applicable Page Date 28 February 2006 914 5 Section 914 Pilot s Operating Handbook GARMIN GTX 327Transponder XTRA EXTRA 300 914 3 EMERGENCY PROCEDURES 914 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 914 4 NORMAL PROCEDURES Not applicable 9145 PERFORMANCE Not applicable 914 6 Page Date 28 February 2006 Pilot s Operating Handbook TR A EXTRA 300 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 ic ziz ipe ET 915 3 Mod Selection Keys IEEE 915 4 Code
83. Instruments 18030 835 0 22 1 75 1 EGT CHT Westach 2DA1 0 07 1 75 1 EGT Probe Westach 712 2 DWK 0 06 0 37 1 CHT Probe Westach 712 7 DK 0 05 0 20 1 Manifold Press United Instruments UI6331 H 186 0 49 1 73 R Fuel Flow Ind 1 VHF Radio Becker AR 3201 0 90 1 67 R 1 VHF Radio Becker AR 4201 0 67 1 67 A 1 GPS COM Garmin GNS 430 2 95 1 61 1 Transponder Filser TRT 600 LAST 0 70 1 61 1 Transponder Filser TRT 800 0 70 1 61 1 Transponder Becker BXP6401 1 0 80 1 67 1 Transponder Becker BXP6401 2 0 80 1 67 1 Transponder Becker ATC 2000 1 20 1 61 1 Transponder Becker ATC 4401 0 73 1 67 1 Transponder Antenna Comant Industries 105 0 11 1 Transponder Bendix King 60 0 11 1 Moba 210FA 0 10 4 90 R 1 COM Antenna Extra 83205A 0 10 4 90 A 1 COM Antenna Pointer P1 3001 10 0 05 4 90 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 Battery Sonnenschein Dryfit A 212 28G 10 70 0 08 R 1 Battery Concorde RG 25XC 10 40 0 08 A 6 12 Page Date 28 February 2006 Pilot
84. N 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 28 February 2006 905 3 Section 905 Pilot s Operating Handbook External Power EXTRA 300 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 DESCRITPION 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 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 External Power Relais Diode By 550 100 cZ 2 ANS CSE AACE CRORE External Power Receptacle AN 2552 3A 12V 28AH Main Relais l E EE BATTERY T T Master Switch Starter Relais STARTER
85. PILOT COPILOT ACRO FUEL WING FUEL W xa X WxX Page Date 20 April 2002 6 7 Section 6 Pilot s Operating Handbook Weight and Balance and Equipment List XTRA EXTRA 300 6 4 LOADING WEIGHTS AND MOMENTS OCCUPANTS max 2 WEIGHT PILOT COPILOT REAR SEAT FRONT SEAT ARM 217cm 85 4 116cm 45 7 MOMENT KG x CM IN x LBS 13020 11273 6960 14105 12212 7540 15190 13152 8120 16275 14091 8700 17360 15030 9280 18445 15970 9860 19530 16909 10440 FUEL MAX 160 LITER 42 3 US GAL CAPACITY WEIGHT MOMENT LITER US GAL KG LBS KG CM INLBS 20 14 4 31 7 792 688 40 28 8 63 5 1584 1375 60 95 3 2333 2025 80 3082 2675 3830 3325 4579 3975 5328 4625 6077 5275 6 8 Page Date 20 April 2002 Pilot s Operating Handbook Section 6 EXTRA 300 XTRA Weight and Balance and Equipment List 6 5 WEIGHT AND MOMENT LIMITS EXAMPLE AT 800 KG 1764 LBS AND 70000 KG CM 60768 IN LBS THE C G LOCATION IS 87 5CM 34 4 AFT OF REF DATUM Weight kg Ibs MAX 0 NORMAL 950 2095 900 1985 MAX T O ACRO II CAT 870 1918 MAX T O I CAT LLL 820 1808 800 1764 700 1544 77777777277 4 Ly 75 76 78 80 82 84 86 88 90 ARM cm 29 5 29 2 30
86. 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 to 60 65 knots A light pressure on the stick lifts the tail to horizontal position Rotate the aircraft at 65 knots On reaching climb speed of 100 knots reduce the RPM and Manifold pressure to 2400 24 and proceed climbing 4 6 CLIMB The maximum continous RPM is restricted to 2400 If not stated somewhere else refer to Section 4 12 Acrobatic Maneuvers the aircraft may be operated in acrobatic maneuvers up to 2700 RPM RPM above 2400 should however be used only for acrobatic maneuvers when necessary for maximum performance in order to avoid unnecessary noise Turn boost pump OFF 4 7 CRUISE 1 Altitude As selected 2 Throttle RPM Adjust for cruising speed 3 Mixture Adjust for minimum fuel consumptio
87. R 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 Page Date 28 February 2006 915 3 Section 915 Pilot s Operating Handbook GARMIN GTX 330 Transponder XTRA EXTRA 300 915 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 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 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
88. SCE CON 915 4 Keys for other GTX 330 915 5 FHUMICTIONDISIAY accesses 915 5 Configuration Mode ERE EPI 915 6 Altitude trend nnns 915 6 Failure ANMUMCIATION 915 6 915 7 EMERGENCY PROCEDURES 915 7 Important 61626 915 7 NORMAL PROCEDURES i enian 915 7 PERFORMANCE 915 7 Page Date 28 February 2006 915 1 Section 915 mE Pilot s Operating Handbook GARMIN GTX 330 Transponder XTRA EXTRA 300 Left blank intentionally 915 2 Page Date 28 February 2006 Pilot s Operating Handbook Posuit Section 915 EXTRA 300 XTRA GARMIN GTX 330 Transponder 915 1 GENERAL The Garmin GTX 330 panel mounted Mode S Transponder is 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 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 It operates on radar frequencies receiving ground ra
89. SPECTION 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 the airplane must be accomplished by licensed personel Page Date 20 April 2002 8 3 Section 8 nad Pilot s Operating Handbook Handling Servicing and Maintenance 300 8 5 SERVICING In addition to the airplane inspection periods 8 2 information for servicing the aircraft with proper oil and fuel is covered in Section 2 Limitations and Section
90. Safety Belt Hooker 1011 230 3 30 2 20 Assy Rear with ratchet 1 Safety Belt Hooker 1011 230 2 90 1 03 R Assy Front 1 Safety Belt Hooker 1011 230 3 30 1 03 A Assy Front with ratchet 2 NAV STROBE LTS Whelen A 600 PG PR 14 0 23 0 87 R 2 Power Supply Whelen 490 0 54 0 87 1 Standard Canopy EXTRA 26301 000 LV 15 00 2 00 R 1 Standard Rudder EXTRA 2 20 1 26 R Pedal System 1 Electric Rudder EXTRA 83600A0 7 45 1 69 A Pedal Adjustment incl 2 Electric Actuator SKF CARR A Pedal Adjust 22x200x1 D12B 1 Long Range Tank EXTRA 83901 1 80 0 59 1 Fuel Shut Off Valve Spruce 104HD 04x4 0 28 0 75 1 Fuel Shut Off Valve Allen 6S 122 0 19 0 75 Page Date 28 February 2006 Section 6 Weight and Balance and Equipment List XTRA Pilot s Operating Handbook EXTRA 300 QTY ITEM MANUFACT P N WEIGHT ARM MARK IF REQUIRED R KG m INSTALLED OPTIONAL O ALTERNAT A 1 Smoke System EXTRA 83100 5 20 0 30 without Pumps 2 Smoke Oil ITT Jabsco 8860 1203 3 60 0 10 Inject and Refill Pump 2 Smoke Oil ITT Jabsco 23620 3003 4 40 0 10 Inject and Refill Pump 1 Smoke Oil Johnson F3B 19 12V 2 00 0 05 Inject Pump 1 Smoke Oil Johnson F2P10 19 12V 1 65 0 25 Refill Pump 1 Airtow Hook EXTRA TOST 83607A0 0 50 5 72 1 2 Sighting Dev EXTRA 83801 10 each 0 54 1 63 1 Aresti Card Holder EXTRA Assy 0 09 1 74 2 Wing Tie Down Rin
91. TONS 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 S 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 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 inter
92. acle 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 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 starting 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 CAUTIO
93. ad weather window OPEN 3 Ventilation OPEN 4 If smoke persists the cockpit land AS SOON AS PRACTICAL NORMAL PROCEDURES The smoke system includes features for refilling the smoke oil tank 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 tank 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 S MOKE REFILL ON NOTE The refilling should start within max 30 sec Ifthis is not the case the refill lines and fittings 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 Page Date 20 September 2001 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 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 H
94. analysis are displayed in the second line LIST OF POSSIBLE ERRORS 1 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 28 February 2006 912 7 Section 912 Pilot s Operating Handbook FILSER TRT 600 Transponder 300 912 2 912 3 912 4 912 5 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 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 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 wit
95. and security CHECK 2 Trailing edge CHECK 3 Fuel tank vent opening right landing gear CHECK 4 Fuel quantity CHECK 5 Fuel tank filler cap CHECK 6 Right landing gear wheel and brake CHECK 7 Stall warning vane CHECK 4 4 Page Date 20 April 2002 Pilot s Operating Handbook Section 4 Normal Procedures 4 Nose 1 Engine oil dipstick 2 Propeller and spinner 3 Air inlet 4 Fuel filter drain CHECK CHECK CHECK DRAIN FOR AT LEAST 4 SECONDS TO CLEAR FILTER OF POSSIBLE WATER CHECK CLOSED 5 Acro fuel tank drain DRAIN 4 SECONDS CHECK CLOSED 6 Exhaust silencer if installed CHECK FOR DAMAGE AND SECURE ATTACHMENT 5 Left wing 1 Left landing gear wheel and brakes CHECK 2 Fuel quantity CHECK 3 Fuel tank filler cap CHECK 4 Pitot cover REMOVE 5 Trailing edge CHECK 6 Aileron freedom of movement and security CHECK 6 Before starting engine 1 Preflight inspection COMPLETE 2 Passenger briefing COMPLETE 3 Parachute handling briefing COMPLETE 4 Seats seatbelts shoulder harnesses ADJUST AND LOCK 5 Canopy CLOSE AND LOCK 6 Brake CHECK 7 Avionics power switch OFF 8 Electrical equipment OFF 9 Alternator ON 10 Wingtip position Strobe lights ON Page Date 20 April 2002 4 5 Section 4 Pilot s Operating Handbook Normal Procedures 300 4 3 STARTING PROCEDURES 4 3 1 COLD ENGINES The following starting procedures are rec
96. anged and no alterations of or additions to the approved contents may be made without the EXTRA Flugzeugproduktions und Vertriebs GmbH LBA approval The editor has the copyright of this Flight Manual and is responsible for edition of revisions amendments and supplements 24 Amendments which affect the airworthiness of the aircraft will be announced in the publication Luftt chtigkeitsanweisung airworthiness directive issued by LBA Luftfahrt Bundesamt or by the manufacturer EXTRA Flugzeugproduktions und Vertriebs GmbH The owner is responsible for incorporating prescribed amendments and should make notes about these on the records of amendments 2 5 Should this Flight Manual get lost inform EXTRA Flugzeugproduktions und Vertriebs GmbH Dinslaken 46569 H nxe Federal Republic of Germany 2 6 Should this Flight Manual be found kindly forward it to the civil board of aviation in the country the aircraft is registered Page Date 28 February 2006 0 3 Section 0 Pilot s Operating Handbook Publication Guidance EXTRA 300 3 WARNINGS CAUTIONS AND NOTES The following definitions apply 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
97. ch 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 FLIGHT 3g Page Date 28 February 2006 2 7 Section 2 Pilot s Operating Handbook Limitations XTRA EXTRA 300 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 11 1 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
98. ci 5 5 AIRSPEED CALIBRATION 5 6 STALL SPEED ge 5 7 TAKE OFF 5 8 RATE CLIMB 5 9 TIME CLIMB FUEL TO CLIMB nior cere eonun nani 5 10 RANGE AND ENDURANCE ae ima eia na ek ana ana nai 5 11 FUEL orc crap 5 12 CRUISE PERFORMANDGE oec meae tenerte iare 5 13 LANDING PERFORMANCE 5 14 Page Date 20 April 2002 Section 5 Performance XTRA Pilot s Operating Handbook EXTRA 300 Left blank intentionally Page Date 20 April 2002 Pilot s Operating Handbook Section 5 EXTRA 300 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
99. creen 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 the Configuration Mode Pressing the VFR key again will restore the previous identification code START STOP Starts and stops the Count Up and Count Down timers CRSR Initiates entry of starting time for the Count Down timer and cancels transponder code entry 914 4 Page Date 28 February 2006 Pilot s Operating Handbook E Section 914 GARMIN GTX 327 Transponder EXTRA 300 914 2 CLR Resets the Count Up and Count Down timers and cancels the previous keypress during code selection 8 Reduces Contrast and Display Brightness when the respective pages are displayed Also enters the number eight into the Count Down timer 9 Increases Contrast and Display Brightness when the respective pages are displayed Also enters the number nine into the Count Down timer FUNC Changes the page shown on the right side of the display Displayed data includes Pressure Altitude Flight Time Count Up timer Count Down timer and may include Contrast and Display Brightness depending on configuration refer to the screen description below SCREEN DESCRIPTION PRESSURE ALT Displays the altitude data supplied to GTX 327 in feet hundreds of feets i e flight level or meters depending on configuration FLIGHT TIME Displays the
100. cters 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 FN XXXXXXXxX 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 28 February 2006 Pilot s Operating Handbook Section 920 EXTRA 300 BECKER 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 andthe same for next digits 7 Fifth push to button C now again first digit is inverted 8 Changes be stored with STO button 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 Code Activation 10 Atimeout for inversion 10 sec is introduced if no action happens Nothing stored
101. d landing A 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 Removal of ELT from A C 0 Pay attention for best E 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 transmission Ensure that whip antenna is clear of obstruction 904 4 Page Date 20 April 2002 Pilot s Operating Handbook Section 904 EXTRA 300 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 REMOVE ELT FROM A C Severed whip antenna cable Danger
102. d a breaking piece weak links of max 850 kp 1875 lbs needs to be interconnected LIMITATIONS For a save air towing the following points must be observed ee EE Takeoff Weight 820 kg 1813 Ibs Max Empty Weight 701 kg 1546 Ibs 2 seats 870 kg 1924 Ibs 665 kg 1466 Ibs 68 KIAS Min Air Towing Speed 66 KIAS Best Air Towing Speed 72 76 KIAS 74 78 KIAS NOTE 2 seats only in case of an instruction flight 1 Maximum air towing speed 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 20 April 2002 908 3 Section 908 2 Pilot s Operating Handbook Airtow Hook 300 908 3 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 1 Pilot of the glider INFORM 2 Air tow RELEASE 3 Airspeed 80 KIAS 4 Mixture IDLE CUT OFF 5 Fuel shutoff valve OFF 6 Ignition switch OFF 7 Master switch OFF 8 Forced landing PERFORM AS PRACTICAL C EXCESSIVE CLIMB OVER BY THE TOWING GLIDER 1 Pilot of the glider INFORM 2 Air tow RELE
103. d within 3 seconds the previous code appears 2 Activation of the VFR codes a Press the 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 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 919 6 Page Date 28 Februar
104. dar interrogations at 1030 MHz and transmitting acoded response of pulses to ground based radar ona frequency of 1090 MHz The GTX 330 equipped with IDENT capability that activates the Special Position Identification SPI pulse for 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 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 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 MASTE
105. ded 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 9171 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 holdingitfortwo seconds will restore the previous identification code When in 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 Whenin 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 wi
106. deral Republic of Germany Exhaust Silencer for standard system PN EA 300 NSD GO3 606500 Complete 6 in 1 System with integrated Silencer PN EA 300 606000 1 6 FUEL Fuel type AVGAS 100 100 LL for alternate fuel grades see later issues of Textron Lycoming 5 1 No 1070 Minimum 100 130 octane Maximum 115 145 octane Total fuel capacity 160 liters 42 3 US Gallon Wingtanks 2 x 60 1 120 liters 31 7 US Gallon Acro tank 1 40 liters 10 6 US Gallon Usable fuel capacity in the system 158 liters 41 US Gallon Usable fuel capacity for acrobatic 38 liters 10 04 US Gallon 1 7 OIL Maximum sump capacity 16 qts Minimum sump capacity Acrobatic 12 qts Normal 9 qts Average ambient air Mil L6082 Mil 22851 temperature grades ashless dispersant grades All temperatures SAE 15W50 or 20W50 gt 27 80 60 gt 16 60 40 60 euo SAE 40 30 F 90 F Page Date 28 February 2006 1 5 1 ead Pilot s Operating Handbook General XTRA EXTRA 300 1 7 OIL CONT Average ambient air Mil L6082 Mil 22851 temperature grades ashless dispersant grades 18C til 21 C SAE 30 SAE 30 40 or 20W40 0 F 70 F 18C til 32 C SAE 20W50 SAE 30 40 or 20W40 0 F 90 F lt 12 C 10 F SAE 20 SAE 30 or 20W30 single or multi viscosity aviation grade oils see latest issue of Textron Lyc S l No 1014 1 8 LOADING Wing loading 88 8 kg m Normal 76 6 81 3 kg m
107. e 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 reset to Og after every single action The Total Extreme Values can be shown or reset 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 00 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 Instantaneous Acceleration is 30 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 Cur rent Extreme Value and the fifth LED in negative direction for the negative Current Ex treme Value The LC Display shows A 9 09 A 50g 903 4 Page Date 20 April 2002 Pilot s Operating Handbook Section 903 EXTRA 300 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 Displa
108. e 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 squitter checks When Flight ID mode the transponder will not reply to any interrogations In addition the display brightness can be manually adjusted by rotating the BRT knob GND Selects the Ground mode displaying GND in the altitude window When in Ground mode the transponder will not reply to ATCRBS ATCRBS Modes 5 All Call and Mode S only All Call interrogations It will continue to generate Mode S squitter transmissions and reply to discretely addressed Mode S interrogations ON Powers on the transponder in Mode A C and S In this mode the transponder replies to interrogations as indicated by the Reply Symbol Replies do not include alti
109. e more than one cumulative hour on or before battery replacement date Page Date 20 April 2002 904 7 Section 904 IL Pilot s Operating Handbook Emergency Locator Transmitter 300 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 905 3 905 2 LIMITATIONS 905 3 905 3 EMERGENCY PROCEDURES pic aano 220 Canon a 905 3 905 4 NORMAL PROCEDURES 905 3 905 5 905 4 905 6 WEIGHT AND BALANCE 222 1141111 905 4 905 7 DESCRITPION OF THE SYSTEM ccsccicsevessseessacesnccccensisqntvstencsceressepecsstsnnvccnattcartestecedice 905 4 905 8 HANDLING SERVICING AND MAINTENANCE eese nennen 905 5 Page Date 20 April 2002 905 1 Section 905 junii Pilot s Operating Handbook External Power XTRA EXTRA 300 Left blank intentionally 905 2 Page Date 20 April 2002 Pilot s Operating Handbook Z Section 905 EXTRA 300 External Power 905 EXTERNAL POWER 905 1 GENERAL The EXTRA 300 can be equipped with two versions of an optional external power recept
110. e possible Mode indication bottom line SBY mode SbY is displayed Mode A ON appears in the display is displayed the duration of the identification function Mode A C ALT ff a valid altitude is present the flight level height in steps of 100 ft preceded by e g F241 24100 ft appears If no valid altitude code is present FN 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 VFR 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 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 28 February 2006 Pilot s Operating Handbook E Section 919 EXTRA 300 BECKER 4401 Transponder 3 After the switch on test has elapsed and error
111. e 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 Page Date 20 April 2002 3 3 Section 3 Pilot s Operating Handbook Emergency Procedures 300 3 1 AIRSPEEDS FOR EMERGENCY OPERATION Stall speed 60 KIAS Engine failure after take off 80 KIAS Best recommended gliding speed glide angle 1 6 2 Normal 950 kg 90 KIAS Acro 820 kg 80 KIAS Precautionary landing with engine power 80 KIAS Landing without engine power 80 KIAS Maximum demonstrated cross wind component 15 Knots 3 2 OPERATIONAL CHECKLIST 3 2 1 ENGINE FAILURE DURING TAKE OFF ROLL 1 Throttle IDLE 2 Brakes APPLY 3 Mixture IDLE CUT OFF 4 Ignition switch OFF 5 Master switch OFF 3 2 2 ENGINE FAILURE IMMEDIATELY AFTER TAKE OFF Stall speed 60 KIAS 1 Airspeed 80 KIAS 2 Mixture IDLE CUT OFF 3 Fuel shutoff valve OFF 4 Ignition switch OFF 5 Master switch OFF 6 Forced landing PERFORM as practical
112. ed 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 NOISE LEVEL The noise level with silencer Gomolzig 606000 6 in 1 and propeller MTV 14 B C C190 17 has been established in accordance 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 LBA 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 28 February 2006 e e Handbook XT R A SECTION 3 EMERGENCY PROCEDURES Table of Contents Paragraph Page 3 0 2 M 3 3 3 0 1 3 3 3 0 2 General Behaviour in Emergency Situations 2 3 3 3 1 AIRSPEEDS FOR EMERGENCY 3 4 3 2 OPERATIONAL CHECKLIST 3 4 3 2 1 Engine Failure During Take off 3 4 3 2 2 Engine Failure Immediately After Take Off 2 3 4 3 2 3 Engine Failure During Flig
113. ed 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 possible 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 28 February 2006 917 3 Section 917 p Pilot s Operating Handbook BENDIX KING KT 76A Transponder 300 917 FUNCTION SELECTOR KNOB Th
114. eeeeeeeeeeeeeene enne enne nnn nennen nnne 2 8 Structural Temperature Colour Limitation sese 2 8 MAXIMUM OPERATING ALTITUDE eeeeeeeseeeeeee eene 2 8 TIRE 50 2 8 MARKINGS AND PLACARDS nnn assent annii nn nina tnn mannna nanenane nann 2 8 Aircraft Identity Placard 2 8 Operating Placards ue terree toco es Re een rd re 2 9 Instument 2 12 KINDS OF OPERATION EQUIPMENT 2 13 2 14 Page Date 28 February 2006 2 1 Section 2 Z Pilot s Operating Handbook Limitations XTRA EXTRA 300 Left blank intentionally 2 2 Page Date 20 April 2002 Pilot s Operating Handbook Section 2 XTRA Limitations EXTRA 300 2 1 2 2 2 3 2 4 SECTION 2 LIMITATIONS 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 Luftfahrt Bundesamt LBA Observance of these operating limitations is required by national aviation regulations NOTE In case of an aircraft equi
115. elevator extending into the fuselage 7 4 Page Date 20 April 2002 Pilot s Operating Handbook mE Section 7 EXTRA 300 X TRA Description and Operation of Aircraft and Systems 7 5 FLIGHT CONTROL SYSTEM 7 5 1 PRIMARY CONTROL SYSTEM The EXTRA 300 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 lubricated 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
116. ellow range gt 10g 80 green range gt 8g 48g yellow range 890 lt 109 red range 10g 129 903 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 20g 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 Pilot s Operating Handbook Electronic Accelerometer EXTRA 300 The other outputdisplay are twentyfive LEDs which are arranged in a semicircle The upper twelve LEDs show positive acceleration the lower twelve LEDs show negative accelera tion 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 120 and 12g If 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
117. er 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 28 February 2006 919 5 Section 919 Pilot s Operating Handbook BECKER ATC 4401 Transponder XTRA EXTRA 300 b Press store push button STO J the set code then flashes Pressthe VFR1 push button F or the push button G wit hin seconds to store the code under the corresponding button d If neither button F 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 switched to active after seconds can be changed in the configuration mode If the same button is again presse
118. failure was found The PBIT takes not longer than 1 second If the test was successful the XPDR switches immediately into the normal operating mode 920 1 7 SELECTION MODE Press SEL button G and rotate encoder B for selection In selection mode additional information is displayed in the bottom line of the display Some of the data are editable some are read only VFR 4096 code presetting editable Al Aircraft Identifier fixed read only from address module an be replaced by Tail Number FN no valid Alis stored is displayed FN Flight Number or editable Company Call Sign can be replaced by AI fixed byselecting Al DEF AA Aircraft Address fixed read only from addressmodule 24 bit ICAO unique number for each aircraft MA Airspeed fixed read only from address module AT Aircraft Type fixed read only from address module CFG Configuration available in SBY mode only INS Installation setup available in SBY mode only protected by password AIRCRAFT IDENTIFICATION AI OR FN With flight plan The definition out of the flight plan e g Flight Number or Company Call Sign Without flight plan VFR Tail Number 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
119. g 4 Switch in the throttle lever for smoke 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 EN o s se s 9 Specific Weight of the paraffin oil 0 85 kg Litre NOTE The smoke system does notfeature a capacity dipstick In the case of unknown filling the smoke oil tank should be drained and refilled with a known quantity If this is not possible the most adverse case has to be taken for CG calculation This may be either completely full or completely empty tank 909 7 DESCRIPTION OF THE SYSTEM On pilot s demand the smoke system produces atrail 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 22 XTRA eer visible as dense smoke after leaving the exhaust For smoke system activation the SMOKE ARM switch located at the pilot instrument panel needs to be switched ON first The smoke ON OFF toggle switch is located on top of the throttle lever For filling the smoke oil tank 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
120. gs EXTRA 83801 2 01 0 04 1 12 6 14 Page Date 28 February 2006 Pilot s Operating Handbook XTR A EXTRA 300 Paragraph 7 1 7 2 7 3 7 4 7 5 7 5 1 7 5 2 7 5 3 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 SECTION 7 DESCPRIPTION AND OPERATION OF AIRCRAFT AND SYSTEMS Table of Contents Page iz ieiup 7 3 gii clc 7 3 Mice 7 4 7 4 FLIGHT CONTROL SYSTEM Sad iamen diee 7 5 Primary Control 7 5 Longitudinal Flight Control System 7 5 Lateral Flight Control re rect En 7 5 Directional Flight Control System 7 5 Secondary COMMON 7 5 INSTRUMENTATION saiisine aane 7 6 Instrument Panel Rear dines 7 6 Instrument Panel Front 7 8 LANDING GEAR 22 7 8 SEATS SEAT BELTS 7 9 7 9 POWER PLANT 7 10 efe
121. h 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 LIMITATIONS Not applicable EMERGENCY PROCEDURES The following emergency codes should be noted 7500 Hijacking 7600 Loss of communication 7700 Emergency NORMAL PROCEDURES Not applicable PERFORMANCE Not applicable 912 8 Page Date 28 February 2006 Pilot s Operating Handbook TR A EXTRA 300 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 913 3 Front Panel 913 3 System 913 5 Error Reporting Fault 913 7 LIMITATIONS 2 913 8 EMERGENCY PROCEDURES 913 8 NORMAL PROCEDURES 2 2
122. he 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 28 February 2006 913 5 Section 913 p Pilot s Operating Handbook FILSER TRT 800 Transponder 300 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 75
123. ht Restart 3 4 3 2 4 Oil 3 5 3 2 5 AlternatorEallute 3 5 3 3 gelez aEucce 3 5 3 3 1 Emergency Landing Without Engine 3 5 3 3 2 Precautionary Landing With Engine eene 3 5 3 4 FRES pec RS 3 6 3 4 1 During Start ECT 3 6 3 4 2 Falls WO iu e xa 3 6 3 4 3 Engine Fire In Ellghit oae 3 7 3 5 E E E 3 7 3 5 1 Inadvertent Icing 3 7 3 6 UNINTENTIONAL SPIN in terna 3 7 3 7 3 7 3 8 EMERGENCY EXIT AFTER TURN 3 8 3 9 ELEVATOR CONTROL FAILURE eeeeeseeeeeee seen seen tnnt natnra nass atra asas manna 3 8 Page Date 20 April 2002 3 1 Section 3 2 Pilot s Operating Handbook Emergency Procedures 300 Left blank intentionally 3 2 Page Date 20 April 2002 Pilot s Operating Handbook mE Section 3 EXTRA 300 Emergency Procedures SE
124. ight 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 7 12 m 23 36 ft 2 62 m 8 60 ft 8 00 m 26 25 ft 1 80 m 5 91 ft 5 02 m 16 47 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 83m 1 404 m 4 61 ft 2 x 0 855 m 2 x 9 20 ft 30 tolerance 2 3 20 m 10 50 ft 2 56 m 27 56 ft Wortmann FX 71 L 150 30 0 77 m 8 29 ft up 25 down 25 tolerance 2 15 tolerance 2 1 39 m 14 96 ft Wortmann FX 71 L 150 30 0 51 m 5 49 ft left 30 right 30 tolerance 2 Page Date 20 April 2002 Pilot s Operating Handbook Section 1 EXTRA 300 XTRA General 1 4 ENGINE Manufacturer Textron Lycoming Williamsport Plant PA 17701 USA a Type Lycoming AEIO 540 L1B5 b Type Lycoming 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 a MTV 9 B C C 200 15 constant speed b Type MTV 14 B C C 190 17 4 constant speed 1 5 1 EXHAUST SYSTEMS OPTIONAL Manufacturer Gomolzig Flugzeug und Maschinenbau GmbH Fe
125. ine 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 28 February 2006 915 5 Section 915 p Pilot s Operating Handbook GARMIN GTX 330 Transponder XTRA EXTRA 300 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 temperature input UP 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 time is entered with the 0 9 keys Pressing 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 in Configuration Mode Contrast is controlled by the 8 and 9 keys DISPLAY This page is only displayed if manual backlighting mode is selec
126. ing 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 20 April 2002 Pilot s Operating Handbook XTR A EXTRA 300 SECTION 4 NORMAL PROCEDURES Table of Contents Paragraph Page 4 0 ilz lzni 4 3 4 0 1 Airspeeds For Normal 4 3 4 0 2 Checklist And nennen trennt nns nnns 4 3 4 1 PREFLIGHT INSPECTION ecce erui 4 4 4 1 1 Exterior Inspection cce ctt rettet rere EL rn in 4 4 4 1 2 General m 4 4 4 2 CHECKLIST PROCEDURES none umen 4 4 4 3 STARTING PROCEDURES m eaa 4 6 4 3 1 4 6 4 3 2 gloss c 4 6 4 4 TAXIING THE AIRCRAFT esee manant anna nnns nnns tasas snnm 4 6 4 5 TAKE OFF 4 7 4 5 1 MEO 4 7 4 5 2 Pm 4 7 4 6 CUIAB 4 7 4 7 RUNS Bie 4 7 4 8 LANDING PRO
127. 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 96g C 83g Page Date 20 April 2002 903 7 Section 903 Pilot s Operating Handbook Electronic Accelerometer XTRA EXTRA 300 Additionaly the long term memory stores the times and dates when new Absolute Extreme Values occure 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 MIN DATE 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 f
128. ions 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 919 4 NORMAL PROCEDURES Not applicable 919 5 PERFORMANCE Not applicable 919 8 Page Date 28 February 2006 Pilot s Operating Handbook TR A EXTRA 300 Paragraph 920 1 920 1 1 920 1 2 920 1 3 920 1 4 920 1 5 920 1 6 920 1 7 920 1 8 920 1 9 920 1 10 920 2 920 3 920 3 1 920 4 920 5 SECTION 920 BECKER ATC 6401 TRANSPONDER Table of Contents Page H 920 3 Controlsand Indicators 920 4 Switching on the Unit pre flight 920 4 M 920 5 Squawk 920 5 Squawk Ident 920 6 Selftests of the Unit 2 2 24 10 00000 ar nnne neni nennen 920 6 Selecion MOG MR 920 7 Flight Operation in Mode A C S reply code and altitude code 920 9 VER Gode Activation 920 10 Configu
129. 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 communications 7700 Emergency Page Date 28 February 2006 920 5 Section 920 p Pilot s Operating Handbook BECKER ATC 6401 Transponder XTRA EXTRA 300 7777 Military interceptor operations Never squawk this code 0000 Military use Not enterable
130. ity W1 Sum of weights indicated by the two scales below the main wheels W2 Weight indicated by the scale below the tail wheel W Total weight W1 W2 XG x X1 W2 x X2 C G position W Reference Firewall plane W W1 W2 XG CKU W2 x 2 Page Date 28 February 2006 Section 6 Weight and Balance and Equipment List XTRA Pilot s Operating Handbook EXTRA 300 If a new weight is added to the known old weight and C G position the resulting new weight and C G can be obtained by a simple calculation Situation before adding item Wo Xo Airplane weight C G position Wn Xn Weight distance from fire wall of item to add New Weight of airplane and new C G W Wo x Xo Wn x Xn C G position 6 2 1 OWNERS WEIGHT AND BALANCE RECORD Enter below all weight change data from aircraft log book EXTRA 300 SERIAL NUMBER REGISTRATION Date Description of Weight change Running empty modification Added Removed weight Wt kg Arm cm Moment kg cm Wt kg Moment kg cm lbs inch Ibs inch lbs lbs inch Empty weight as delivered Page Date 20 April 2002 Pilot s Operating Handbook EXTRA 300 Section 6 Weight and Balance and Equipment List 6 3 CENTER OF GRAVITY CALCULATION SAMPLE PROBLEM PILOT REAR SEAT kg
131. ixture control Throttle lever Intercom button Stick Radio button Fuel shutoff valve Trim lever and indicator Master switch Boost pump Directional gyro This list may be modified by the minimum equipment requirements of individual certifying authorities Page Date 20 April 2002 7 Pilot s Operating Handbook Description and Operation of Aircraft and Systems X TRA EXTRA 300 7 6 2 INSTRUMENT PANEL FRONT COCKPIT Normally the instument panel in the front cockpit is only equipped with the following positions 2 Airspeed indicator 9 Altimeter indicator 23 Throttle 24 Intercom button 25 Stick 26 Radio button 27 Fuel shutoff valve 7 7 LANDING GEAR The landing gear is a composite construction with a multichamber fiberglass 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 mE Section 7 EXTRA 300 X TRA Description and Operation of Aircraft and Systems 7 8 SEATS SEAT BELTS The seat in the rear cockpit is mechanically adjustable on the ground The 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 Seat to pedal distance can be varied on the ground in differe
132. l 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 buiton 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 before the button was pressed 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 R Masks L H 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 Page Date 20 April 2002 906 5 Section 906 Pilot s Operating Handbook Digital RPM Indicator XTRA EXTRA 300 Quickly pressing and releasing the left button L causes the tachometer to mask the left tachometer Quickly pressing and releasing the right button R causes the tachometer to mask the right tachometer Dimmer D M Quickly pressing and releasing the
133. le in order to avoid exceeding Ve Above segments may be filled up with aileron rolls on snap rolls Watch V 158 KIAS for aileron rolls with max deflection Snap rolls should not be performed at speeds above 140 KIAS Segment 1 4 loop climbing The minimum recommended speed is 100 KIAS 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 NOTE Since the maximum horizontal speed is 185 KIAS 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 20 April 2002 4 11 Section 4 Pilot s Operating Handbook Normal Procedures XTRA EXTRA 300 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 4 12 3 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
134. lert 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 min is 175 The maximal difference between the magnetos has not to be over 50 RPM identify with the illuminated yellow LED Page Date 20 April 2002 906 3 Section 906 25 Pilot s Operating Handbook Digital RPM Indicator XTRA EXTRA 300 906 5 PERFORMANCE Not affected 906 6 WEIGHT AND BALANCE Not affected 906 7 DESCRIPTION AND OPERATION OF THE SYSTEM The operation of the indicator is straightforward After power is supplied to the indicator the engine is started and the self tests are performed 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 _Magneto Control RPM range NU ES CU RPM eo b restriction Operation placard Press and hold Operation placard Press and release RPM RANGES Engine operating ranges are indicated on the large green yellow
135. ll 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 28 February 2006 917 5 Section 917 p Pilot s Operating Handbook BENDIX KING KT 76A Transponder 300 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 1D FUNCTION DISPLAY 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 addition the ID code is displayed in the right window the ident window A faultin 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 o
136. lock 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 Pilot s Operating Handbook Electronic Accelerometer XTRA EXTRA 300 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 Button S2 Contrast LC Display Bright 1 THE FIRST 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 09 A 0 0g 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 positve and another one indicates the negative Current Extreme Value The
137. middle button D M causes the tachometer to alter nately dim or brighten the LED indicators except the large red LED of the RPM Range 906 8 HANDLING SERVICING AND MAINTENANCE Not affected 906 6 Page Date 20 April 2002 Pilot s Operating Handbook XTR A EXTRA 300 Paragraph 907 1 907 2 907 3 907 4 907 5 907 6 907 7 907 8 SECTION 907 LONG RANGE WING TANK CAPACITY Table of Contents Page cii zbl 907 3 LIMITATIONS con 907 3 EMERGENCY PROCEDURES 907 3 NORMAL PROCEDURES scnreecdneatacenantsann cesnensaunesedcessucenents 907 3 udzehliie 907 4 WEIGHT AND BALANCE recur 907 5 DESCRIPTION OF THE SYSTEM 2 nd oo nae nua ku Roca 907 5 HANDLING SERVICING AND MAINTENANCE 907 5 Page Date 20 April 2002 907 1 Section 907 IL Pilot s Operating Handbook Long Range Wing Tank Capacity 300 Left blank intentionally 907 2 Page Date 20 April 2002 Pilot s Operating Handbook Section 907 XTRA Long Range Wing Tank Capacity EXTRA 300 907 907 1 907 2 907 3 907 4 LONG RANGE WING TANK CAPACITY GENERAL The leading edge
138. n 4 Trim As required 5 Fuel Check periodically Page Date 20 April 2002 4 7 Section 4 Normal Procedures XTRA Pilot s Operating Handbook EXTRA 300 4 8 LANDING PROCEDURES 4 8 1 DESCENT 1 Throttle Reduce 2 Mixture FULL RICH 3 RPM Control Set to 2400 RPM 4 Trim Adjust 4 8 2 APPROACH 1 Boost pump ON 2 Mixture set to RICH 3 Airspeed reduce to approach speed 4 Propeller set to low pitch HIGH RPM NOTE It is recommended to set the RPM to 2400 during approach and landing in order to avoid unnecessary noise In case of Go Around RPM control must be set to max RPM before applying power 4 8 3 BEFORE LANDING 1 Landing approach proceed 2 Airspeed on final maintain 78 KIAS 3 Elevator trim adjust NOTE Stall speed will be MTOW 820 kg 55 KIAS MTOW 870 kg 57 KIAS MTOW 950 kg 60 KIAS 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 28 February 2006 Pilot s Operating Handbook Section 4 EXTRA 300 Normal Procedures NOTE The rudder is effective down to 30 KIAS 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
139. n optional elect pedal adjustment system The pedal adjustment system provides an in flight capabil ity 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 control 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 in flight 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
140. n 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 5 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 1E PROGRAMMING MODE The programming mode is normally set at time 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 1F AIR GROUND SWITCHING The AUTO GND Automatic Ground Programming function is not available 917 6 Page Date 28 February 2006 Pilot s Operating Handbook hend Section 917 EXTRA 300 XTRA BENDIX KING KT 76A Transponder 917 1G 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
141. n 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 2596 of the aileron depth 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 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 caps and GRP laminates The shell is built by honeycomb sandwich with GRP laminates Buckling is prevented by plywood ribs 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
142. ndicated 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 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 ATC 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 Page Date 28 February 2006 918 5 Section 918 mE Pilot s Operating Handbook BECKER 2000 Transponder XTRA EXTRA 300 918 4 NORMAL PROCEDURES Not applicable 918 5 PERFORMANCE Not applicable 918 6 Page Date 28 February 2006 Pilot s Operating Handbook TR A EXTRA 300 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
143. nds 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 for 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 n
144. normal operation and for emergency release The starter magneto switch is located on the lower edge of the instrument panel in front of the rear seat Page Date 20 April 2002 7 5 7 Pilot s Operating Handbook Description and Operation of Aircraft and Systems X TRA EXTRA 300 7 6 INSTRUMENTATION The Extra 300 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 instrumet panel arrangement of the reat cockpit refer to Fig 7 6 1 which includes standard and optional equipment marked as such Fig 7 6 1 7 6 Page Date 20 April 2002 Pilot s Operating Handbook EXTRA 300 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 X Vertical speed indicator Air speed indicator Turn and bank indicator Manifold pressure Fuel Flow RPM indicator Magn Direction indicator COM Altimeter Artificial horizon Amperemeter Oil pressure Oil temperature Fuel pressure Fuel Quantity Wing Tank Quantity Aero Tank g meter EGT CHT Magneto Selector switch amp starter RPM control Prop governor M
145. nsponder 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 FLOOO 00008 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 flag BAT 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 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 refer to your national aviation authority to apply for your aircraft address 912 6 Page Date 28 February 2006 Pilot s Operating Handbook E Section 912 EXTRA 300 XTRA FILSER TRT 600 Transponder The Aircraft Ide
146. nt positions which can be adjusted with the bolts located on the r h and l h pedal adjustment In the front cockpit there is no possibility to adjust either the pedals nor the seat The seat belt assembly consists of right and left shoulder straps two right and two left lap belts and a negative G strap All belts are adjustable The lap belts have a seperate single point release for redundant safety during acrobatic maneuvers If one release is opened unintentionally the second one guarantees full safety To assure safe operation one release must be closed to the right the other one to the left During acrobatic maneuvers the seat belt system should be tightened firmly 7 9 CANOPY The canopy of front and rear cockpit is manufactured in one section The canopy can be manually operated and opened by lifting to the right In the open position there is a rod mounted to the fuselage rear of the canopy which must be connected to the canopy preventing slam down unintentionally Interior canopy locking handles located on the left side on the canopy of each cockpit must be pulled together to unlock the canopy from the inside To open the canopy from the outside there are no seperate handles this means it must be opened by reaching through the small window bad weather window and proceed as mentioned above interior opening Page Date 20 April 2002 7 9 7 Pilot s Operating Handbook Description and Operation of Aircraft and
147. ntification 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 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 number of the aircraft The pilot has to change the FID manually if necessary 912 1 3 ERROR REPORTING FAULT CODES The transponder 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
148. of this Pilot s Oper ating Handbook Each Supplement section e g steerable tailwheel covers only a single system device or piece or equipment and is 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 performed The Table of Contents shows all EXTRA Supplements available for the EXTRA 300 A check mark in the Section column indicates that the corresponding supplement must be included in this POH Page Date 28 February 2006 9 3 Section 9 Pilot s Operating Handbook Supplements 300 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 GENERAL 901 3 901 2 LIMITA ONS 2 2 M 901 3 901 3 EMERGENCY PROCEDURES 901 3 901 4 22020 04 901 3 901 5 PERFORMANCE m 901 3 901
149. ol 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 some airspaces Mode S Elementary Surveillance functionality is required Date 28 February 2006 2 13 Section 2 XIRA 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 li E 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 the equipment and or system was 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 observ
150. ommended 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 HOT 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 300 Normal
151. on 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 28 February 2006 Pilot s Operating Handbook Z Section 913 EXTRA 300 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 on ground 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 engines 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 t
152. on of Aircraft and Systems X TRA EXTRA 300 Left blank intentionally 7 16 Page Date 20 April 2002 e e Handbook XIR A SECTION 8 HANDLING SERVICING AND MAINTENANCE Table of Contents Paragraph Page 8 1 ll ggiejsjeie m 8 3 8 2 AIRPLANE INSPECTION PERIODS 7 oen nn canna kann cain e nana an nan nik asap an 8 3 8 3 PILOT CONDUCTED PREVENTIVE MAINTENANCE 24 442422 2 8 3 8 4 ALTERATIONS OR 8 3 8 5 8 4 8 6 GROUND rpillcm 8 4 Page Date 20 April 2002 8 1 Section 8 m Pilot s Operating Handbook Handling Servicing and Maintenance 300 Left blank intentionally 8 2 Page Date 20 April 2002 Pilot s Operating Handbook Section 8 EXTRA 300 XTRA Handling Servicing and Maintenance SECTION 8 HANDLING SERVICING AND MAINTENANCE 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 IN
153. 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 300 904 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 switch 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 ELT mounting bracket Remote switch optional 904
154. ontents Paragraph Page 909 1 909 3 909 2 909 3 909 3 EMERGENCY 909 3 909 4 NORMAL PROCEDURES 909 4 909 5 dsgeulL ie 909 5 909 6 WEIGHT AND BALANCE 909 5 909 7 DESCRIPTION OF THE SYSTEM wescsccseccecesescncecceccesecesnsnessanseracceseuneectcensiceuecrendncdeaneesandes 909 5 909 8 HANDLING SERVICING AND 2 4 44242222 909 6 Page Date 20 September 200 309 Left blank intentionally ZXTRA NE 909 909 1 909 2 909 3 SMOKE SYSTEM GENERAL For performing at airshows the EXTRA 300 may optionally be equipped with a smoke system LIMITATIONS For safe operation of the smoke system the following limitations have to be considered 1 The load factor is limited to 8g 8q 2 Max takeoff weight MTOW 870 kg 3 Specification of the smoke oil Straight paraffin oil viscosity 30 50cts at 20 C 68 F initial boiling point gt 330 626 F For example Fauth 05 Texaco Canopus 13 or equivalent 4 Local airfield and weather conditions have to be
155. ontroller 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 28 February 2006 919 7 Section 919 p Pilot s Operating Handbook BECKER ATC 4401 Transponder XTRA EXTRA 300 3 A further 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 evaluation are tested on correct function in the SBY ON and ALT modes 4 Incase of a failure appears the report e g E10 in the top line of the display Switch OFF the transponder at such E fault indications 919 1 8 CONFIGURATION MODE The configuration Mode is used to set the unit on the ground and must not be called up in flight Refer to BECKER s Pilot s Guide for further information 919 2 LIMITATIONS Not applicable 919 3 EMERGENCY PROCEDURES 919 3 1 IMPORTANT CODES 7600 Loss of communicat
156. ook Section 903 EXTRA 300 X TRA Electronic Accelerometer back 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 absolut 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 IL Pilot s Operating Handbook Electronic Accelerometer EXTRA 300 Left blank intentionally 903 10 Page Date 20 April 2002 7 Handbook XTR A SECTION 904 EMERGENCY LOCATOR TRANSMITTER Table of Contents Paragraph Page 904 1 GENERAL 904 3 904 2 LIMITATIONS 904 3 904 3 EMERGENCY PROCEDURES 904 3 904 4 NORMAL PROCEDURES 1 aiamaa na eana pao Fa Ran DN ana anii AEn enin pas 904 5 904 5 PERFORMANCE mem 904 6 904 6 WEIGHT AND BALANCE 904 6 904 7 DESCRIPTION AND OPERATION OF THE SYSTEM
157. or 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 28 February 2006 Pilot s Operating Handbook TR A EXTRA 300 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 m 914 3 Mode Selection Keys eet aet 914 3 Gode ein 914 4 Keys for other GTX 927 9
158. or obtaining the proper license before using the transponder Refer to Becker Pilot s Guide Page Date 28 February 2006 920 3 Section 920 Pilot s Operating Handbook BECKER ATC 6401 Transponder XTRA EXTRA 300 920 1 1 CONTROLS AND INDICATORS 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 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 IDT 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 in the bottom row additional indicators on the left side see Ref H F 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
159. our 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 S1 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 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 903 8 Page Date 20 April 2002 Pilot s Operating Handb
160. p 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 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 noise suppressed to ensure satisfactory operation of the radio equipment All wires switches circuit breakers etc are manufactured to related aeronautical specifications Page Date 28 February 2006 7 13 Section 7 2 Pilot s Operating Handbook Description and Operation of Aircraft and Systems X TRA EXTRA 300 1 TWLS 11 AVN DNIA Standard Equipment shown only 17 3 0815 DNIA AWG 20 q TTD UU 4 4 4 28AH STARTER a AWG 20 7 14 Page Date 28 February 2006 Pilot s Operating Handbook mE Section 7 EXTRA 300 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 15 7 Pilot s Operating Handbook Description and Operati
161. 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 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 Page Date 20 April 2002 902 3 Section 902 Pilot s Operating Handbook Electric Pedal Adjustment XTRA EXTRA 300 the slide tube attachment A full travel from the most rearward to the most forward position takes approximately 15sec I PEDALADJUST FORWARD O CONTROL SWITCHES BACKWARD 902 8 HANDLING SERVICING AND MAINTENANCE Not affected 902 4 Page Date 20 April 2002 Pilot s Operating Handbook XTR A EXTRA 300 Paragraph 903 1 903 2 903 3 903 4 903 5 903 6 903 7 903 8 SECTION 903 ELECTRONIC ACCELEROMETER Table of Contents Page ej i M 903 3 LIMITATIONS me
162. ponder 6 p BENDIX KING 73 Transponder eese esee nennen nnne nnn nannten 8 p BECKER 2000 Transponder 6 p BECKER 4401 Transponder 8 p BECKER 6401 Transponder 10 p Page Date 28 February 2006 9 Section 9 Pilot s Operating Handbook Supplements 300 Left blank intentionally 9 2 Page Date 20 April 2002 Pilot s Operating Handbook Section 9 EXTRA 300 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 LBA for the EXTRA 300 Pages and contents of this section may not be exchanged and alterations of or additions to the approved contents may not be made without the EXTRA Flugzeugproduktions und Vertriebs GmbH LBA approval The editor has the copyright of this Supplements and is responsible for edition of revisions The log of effective pages is found under section 0 4
163. ponder XTRA EXTRA 300 Left blank intentionally 915 8 Page Date 28 February 2006 Pilot s Operating Handbook TR A EXTRA 300 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 916 3 Code SSIS CUON eaea 916 3 GIJN 916 4 Testing the AGA 916 4 LIMITATIONS es 2222025 cS 916 4 EMERGENCY 916 4 NORMAL PROCEDURE cerae trente nuns sesecceesexesueesetecseecueeeesesceess 916 5 916 5 PERFORMANCE inci viscose 916 5 Page Date 28 February 2006 916 1 Section 916 mE Pilot s Operating Handbook BENDIX KING KT 76A Transponder XTRA EXTRA 300 Left blank intentionally 916 2 Page Date 28 February 2006 Pilot s Operating Handbook 2 Section 916 EXTRA 300 XTRA BENDIX KING KT 76A Transponder 916 1 GENERAL BENDIX KING KT 76A panel mounted transponder receives interrogations at 1030 2 and these trigger a coded response of radar pulses which are transmitted back to ATC at 1090 MHz The return reinforces your aircrafts image or blip on the controller s radar screen The KT 7
164. pped 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 LBA Flugzeug kennblatt Nr 1086 Type Certification Data Sheet T C D S 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 AIR SPEED IAS Never Exceed Speed VNE 220 knots Max Structural Cruising Speed VNO 158 knots Maneuver Speed Normal Cat VA 140 knots Maneuver Speed Acro Acro II VA 158 knots CROSS WIND COMPONENT Max demonstrated cross wind component for take off and landing 15 knots ENGINE Engine type Textron Lycoming AEIO 540 L 185 AEIO 540 L1B5D with rated maximum 300 HP 2700 RPM Page Date 20 April 2002 2 3 Section 2 Pilot s Operating Handbook Limitations XTRA EXTRA 300 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 160 litres 42 3 US Gallon Usable fuel capacity 158 litres 41 7 US Gallon For acrobatic flight wing tanks must be empty Total fuel capacity for acrobatic 40 litres 10 6 US Gallon in acro tank Usable fuel capacity for acrobatic 38 litres 10 04 US Gallon
165. 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 turoulence 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 variables 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 The performance figures below are given under following 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 DEFINITION 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 Temperature 15 C Wind Component Headwind 8KT Field Length 3000 ft CRUISE CONDITIONS Total Distance 400 NM Pressure Altitude 8000 ft Temperature ISA 1 C Page Date 20 April 2002 5 3 Section 5 Pilot s Operating Handbook Performance XTRA EXTRA 300 TAKE O
166. pril 2002 Pilot s Operating Handbook Z Section 5 EXTRA 300 XTRA Performance 5 2 ISA CONVERSION ISA Conversion of pressure altitude and outside air temperatur TEMPERATURE 80 40 0 40 80 120 16 15 14 x 132 12 a wd T a 10 9 5 8 3 7 6 5 5 T a 4 3 2 1 60 40 20 0 20 40 60 TEMPERATURE Page Date 20 April 2002 5 5 Section 5 Pilot s Operating Handbook Performance XTRA EXTRA 300 5 3 kts IBS INDIGBHTED AIRSPEED 220 210 200 190 180 AIRSPEED CALIBRATION 170 160 150 140 130 120 110 100 90 80 70 60 60 80 100 120 140 160 180 200 CAS CALIBRATED AIRSPEED kts NOTE Indicated airspeed assumes zero instrument error Page Date 20 April 2002 Handbook R A Section 5 Performance 5 4 STALL SPEED CONDITION POWER IDLE FORWARD C G STALL SPEEDS ANGLE OF BANK WEIGHT CATEGORY 0 30 45 1g 1 159 1 419 950 Normal KIAS KIAS KIAS 2095 Ibs 60 65 72 870 kg ACRO 2 seat KIAS KIAS KIAS 1918 lbs 57 61 68 820 kg ACRO 1 seat 5 5 5 1808 Ibs 55 59 65 Max altitude loss during stall recovery is approximately 100 ft Page Date 20 April 2002 Sec
167. range 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 28 February 2006 918 3 Section 918 p Pilot s Operating Handbook BECKER ATC 2000 Transponder XTRA EXTRA 300 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 transmitter 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
168. ration Mode 2 4204424 0 00 enn 920 10 LIMITATIONS 920 10 EMERGENCY PROCEDURES 920 10 Important COGS e 920 10 NORMAL 5 250 dread 920 10 usen huigu7 920 10 Page Date 28 February 2006 920 1 Section 920 mE Pilot s Operating Handbook BECKER 6401 Transponder XTRA EXTRA 300 Left blank intentionally 920 2 Page Date 28 February 2006 Pilot s Operating Handbook 2 Section 920 EXTRA 300 BECKER 6401 Transponder 920 1 GENERAL The Becker panel mounted ATC 6401 Transponder is 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 5 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 ATC 6401 is equipped with IDENT capability that activates the Special Position Identification SPI pulse NOTE The ATC 6401 owner accepts all responsibility f
169. ricating Additionally all parts of the tailwheel have to be inspected visually for deforma tions cracks and corrosion 901 4 Page Date 20 April 2002 Handbook R A SECTION 902 ELECTRIC PEDAL ADJUSTMENT Table of Contents Paragraph Page 902 1 GENE RAD 902 3 902 2 DRE 902 3 902 3 EMERGENCY 902 3 902 4 NORMAL PROCEDURES wiccsiecciicecccecesstecsteceescersteeestsctsccceseceedeccasccsenteecteereetiesccevsecevadees 902 3 902 5 PERFORMANCE e 902 3 902 6 WEIGHT AND BALANCE yam k annu auc a 902 3 902 7 DESCRIPTION OF THE SYSTEM erecto ana eorr un ca dam eau noma 902 3 902 8 HANDLING SERVICING AND MAINTENANCE 902 4 Page Date 20 April 2002 902 1 Section 902 IL Pilot s Operating Handbook Electric Pedal Adjustment EXTRA 300 Left blank intentionally 902 2 Page Date 20 April 2002 Pilot s Operating Handbook Section 902 XTRA Electric Pedal Adjustment EXTRA 300 902 902 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 can be equipped with a
170. rogations the letter R is displayed on the left top side of the display 912 4 Page Date 28 February 2006 Pilot s Operating Handbook E Section 912 EXTRA 300 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 whether the aircraft is in on ground 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 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
171. rvice station is allowed to enter or change the ICAO aircraft address If you do nothave the ICAO aircraft address Please refer to your national aviation authority to apply for your aircraft address 913 6 Page Date 28 February 2006 Pilot s Operating Handbook 2 Section 913 EXTRA 300 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 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 number of the aircraft The pilot has to change the FID manually if necessary 913 1 3 ERROR REPORTING FAULT CODES The transponder s reception
172. s It operates on radar frequencies receiving ground radar interrogations at 1030 MHz and transmitting acoded response of pulses to ground based radar ona frequency of 1090 MHz The ATC 4401 is equipped with IDENT capability that activates the Special Position Identification SPI pulse NOTE The 4401 owner accepts all responsibility for obtaining the proper license before using the transponder Refer to Becker Pilot s Guide Page Date 28 February 2006 919 3 Section 919 Pilot s Operating Handbook BECKER ATC 4401 Transponder XTRA EXTRA 300 919 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 5 position Standby mode is switched on ON position Mode Ais switched on ALT position Mode A C is switched on Rotary coding switch Control of the cursor in one of the 4 code digits or 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 ldt appears in the bottom line of the LC display E 2 line LC display Code indication top line Codes from 0000 to 7777 ar
173. t 7 2 FUSELAGE The fuselage structure consists of a steel tube construction integrating the wing and empennage connections as well as the seats The front part of the fuselage the lower side and the sides below the wings are faired with aluminium sheet metal In the area of the rear seat there are Lexan windows in the fairing The rear part of the fuselage is covered with Ceconite 102 The upper fuselage body surface consists of a kevlar laminate The canopy is one part The canopy frame is constructed by carbon laminate the correlated frame on the fuselage by GRP The canopy opens to the right and is held in the open position by a belt Emergency jettisonning is achieved by simply unlatching the canopy Page Date 28 February 2006 7 3 7 Pilot s Operating Handbook Description and Operation of Aircraft and Systems X TRA EXTRA 300 7 3 WINGS The wing is of CRP 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 connectio
174. t At ISA Conditions PA Eng Manif Power Setting Fuel TAS IAS Endur Range Mixture Press Consumption ft RPM IN HG 96 Hp l h gal h Kts Kts h NM Best 2000 2400 25 1 75 225 68 7 18 2 167 6 160 2 40 401 Power 2200 24 2 65 195 50 13 3 159 3 152 3 27 520 Economy 2000 23 5 55 165 42 6 11 3 150 2 144 3 88 582 Economy 2000 20 2 45 135 36 5 9 6 139 9 134 4 52 632 Economy 4000 2400 24 6 75 225 68 7 18 2 170 9 158 2 40 408 Power 2200 23 7 65 195 50 13 3 162 4 150 3 26 527 Economy 2000 23 0 55 165 42 6 11 3 153 1 142 3 86 589 Economy 2000 19 7 45 135 36 5 9 6 142 6 133 4 52 640 Economy 6000 2200 23 2 65 195 50 5 13 3 165 6 149 3 24 533 Economy 2000 22 5 55 165 42 6 11 3 156 1 141 3 84 598 Economy 2000 19 3 45 135 36 5 9 6 145 4 131 4 46 647 Economy 8000 2350 21 5 65 195 52 0 13 7 169 0 147 3 14 525 Economy 2050 21 4 55 165 43 0 11 4 159 3 139 3 78 598 Economy 2000 18 8 45 135 36 5 9 6 148 4 130 4 44 655 Economy 10000 2150 19 9 55 165 43 7 11 5 162 5 138 3 70 595 Economy 2000 18 4 45 135 36 5 9 6 151 4 129 4 41 663 Economy 12000 2300 18 3 55 165 45 2 11 9 165 9 136 3 56 583 Economy 2000 17 9 45 135 36 5 9 6 154 5 127 4 37 681 Economy 14000 2075 17 7 45 135 37 1 9 8 157 8 122 4 27 664 Economy NOTE 7 For temperatures above below Standard ISA increase decrease Range 1 7 Endurance 1 196 for each 10 C abo
175. t 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 O ft 1000 ft 2000 ft 3000 ft 4000 ft 5000 ft 6000 ft 7000 ft 8000 ft Tow force glider with m 600 Kg 0 ft 1000 ft 2000 ft 3000 ft 4000 ft 5000 ft 6000 ft 7000 ft 8000 ft Tow force glider with m z 765 Kg 0 ft 1000 ft 2000 ft 3000 ft 4000 ft 5000 ft 6000 ft 7000 ft 8000 ft 908 6 Page Date 20 April 2002 Pilot s Operating Handbook Section 908 EXTRA 300 Airtow Hook 908 6 WEIGHT AND BALANCE Not affected 908 7 DESCRIPTION OF THE SYSTEM The release 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 Page Date 20 April 2002 908 7 Section 908 IL Pilot s Operating Handbook Airtow Hook 300 Left blank intentionally 908 8 Page Date 20 April 2002 Due XTRA SECTION 909 SMOKE SYSTEM Table of C
176. te 20 April 2002 EXTRA 300 Pilot s Operating Handbook Section 906 XTRA Digital RPM Indicator 906 906 1 906 2 906 3 906 4 DIGITAL RPM INDICATOR GENERAL The EXTRA 300 can be equipped with the optional P 1000 Digital RPM indicator alternativ to the mechanical VDO RPM indicator LIMITATIONS The operation limitations are not affected due to the installation of the P 1000 Digital RPM indicator The face of the indicator is placarded with the unchanged Engine RPM operating range Additional 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 240 Green ellow Red 700 2400 2700 EMERGENCY PROCEDURES Not affected NORMAL PROCEDURES The Normal Procedures have to be changed in Chapter 4 5 Take Off Procedure section 4 5 1 Before take off If 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 Left red LED illuminates Display shows RPM drop Ignition switch position RIGHT Status area Right red LED illuminates Display shows RPM drop Ignition switch position BOTH Status area Right and left red LED off illuminate The middle LED is not allowed to a
177. te 20 April 2002 1 7 1 Pilot s Operating Handbook General XTRA EXTRA 300 Left blank intentionally 1 8 Page Date 20 April 2002 Pilot s Operating Handbook XTR A EXTRA 300 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 er G 2 3 Diiigzdzpum 2 3 CROSS WIND COMPONENT 2 3 cR 2 3 ail EET 2 4 5 cL 2 4 PROPELLER 00 2 5 WEIGHT El pe EE 2 5 WEIGHT AND ENVELOPE 11 ecrire 2 5 Normal Fights Em 2 5 Acrobatic Fight 1 Seat eae ee eset 2 5 Acrobatic Flight 2 Seal erret tt e 2 6 ACROBATICMANEQUVERS aa aaa aaaea 2 6 Normal PHON 2 6 EE 2 6 LOAD FACTOR 2 7 m 2 7 Acrobatic zl o j DS 2 8 FLIGHT CREW LIMITS reir eerie ete oi einen I 2 8 KINDS OF OPERATIONAL LIMITS eeee
178. ted 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 latest revision 915 1 6 ALTITUDE TREND INDICATOR When the PRESSURE page 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 FAILURE ANNUNCIATION If the unit detects an internal failure the screen displays FAIL 915 6 Page Date 28 February 2006 Pilot s Operating Handbook 7 Section 915 300 XTRA GARMIN GTX 330 Transponder 915 2 LIMITATIONS Not applicable 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 28 February 2006 915 7 Section 915 mE Pilot s Operating Handbook GARMIN GTX 330 Trans
179. th 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 available is utilized to enhance the tracking capabilities of the ATC facility therefore care should be taken when making routine code changes 914 1 3 KEYS FOR OTHER GTX 327 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 s
180. 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 28 February 2006 912 5 Section 912 p Pilot s Operating Handbook FILSER TRT 600 Transponder 300 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 in the mode indicator field The tra
181. tion 5 Pilot s Operating Handbook Performance XTRA EXTRA 300 5 5 TAKE OFF PERFORMANCE Power T O Power Runway Concrete NOTE For every 5 kts headwind the T O distance can be decreased by 4 For every 3 kts Tailwind up to 10 kts the T O distance is increased by 1096 On a solid dry and plain Grass Runway the T O is increased by 15 OAT 0 32 F 15 C 59 F 30 C 86 F T O Rotat PA T O T O T O T O T O T O weight ing Roll over Roll over Roll over Speed 50 ft 50 ft 50 ft kg Ibs KIAS ft m ft m ft m ft m ft m ft m ft 950 65 SL 96 315 207 679 115 377 248 813 133 436 285 935 2095 2000 115 377 248 814 138 453 298 978 160 525 342 1122 4000 138 453 298 978 166 545 357 1171 192 630 410 1345 6000 166 545 358 1175 199 653 429 1407 230 755 492 1614 870 62 SL 78 256 167 548 93 305 200 656 107 351 230 755 1918 2000 94 308 200 656 112 367 240 787 128 420 276 906 4000 112 367 241 791 134 440 288 945 154 505 331 1086 6000 135 443 289 948 161 528 346 1135 185 607 397 1302 820 60 SL 67 220 114 374 79 259 170 558 93 305 200 656 1808 2000 80 262 173 568 95 312 204 669 112 367 240 787 4000 97 318 207 679 114 374 248 814 134 440 288 945 6000 116 381 249 817 137 449 294 965 161 528 347
182. 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 Error is displayed on the lowest 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 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 28 February 2006 913 7 Section 913 p Pilot s Operating Handbook FILSER TRT 800 Transponder 300 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 err
183. tude information ALT Powers on the transponder in Mode A C 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 standard pressure altitude received from a separate encoder 917 1B CODE SELECTION 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 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 917 4 Page Date 28 February 2006 Pilot s Operating Handbook Section 917 EXTRA 300 XTRA BENDIX KING KT 76A Transponder 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 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 deco
184. uld 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 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 Page Date 28 February 2006 914 3 Section 914 Pilot s Operating Handbook GARMIN GTX 327Transponder XTRA EXTRA 300 914 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 four
185. uselage 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 rear web 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 go on with the preflight checklist a Below 72 C 161 6 F b At 72 C 161 6 F or above STRUCTURAL i eae STRUCTURAL 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 to 111 F at sea level It is possible to start the engine using the aircraft battery at 20 C 4 F without preheating Below 10 C 14 F OAT a special oil breather line must be adapted available as ki
186. ush buttons Page Date 28 February 2006 913 3 Section 913 p Pilot s Operating Handbook FILSER TRT 800 Transponder 300 5 Four rotating knobs used to select the IDENT CODE The assignments 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 5 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 S 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 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 butt
187. ust behind the firewall The acro tank is connected with the wingtanks in a gravity feed system 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 auxiliary pump Switch is located on the instrument panel in the rear cockpit A fuel filter with drain is installed between the fuel shut off and the valve auxiliary fuel pump At the lowest point of the fuel system bottom of acro tank the water can be drained with another drainer Normal float type transducers and electrically operated fuel indicators are used 7 12 Page Date 28 February 2006 Pilot s Operating Handbook mE Section 7 EXTRA 300 X TRA Description and Operation of Aircraft and Systems 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 am
188. ve 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 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 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 4 Page Date 20 April 2002 Pilot s Operating Handbook EXTRA 300 Section 907 Long Range Wing Tank Capacity 907 6 WEIGHT AND BALANCE LOADING WEIGHTS AND MOMENTS FUEL 194 L 51 2 US GAL CAPACITY Liter US GAL 20 5 3 40 10 6 60 15 9 80 21 2 100 26 4 120 140 37 0 160 42 3 180 47 5 194 51 2 WEIGHT KG LBS 14 4 31 7 28 8 63 5 43 2 95 3 57 6 127 0 72 0 158 8 86 4 190 5 100 8 222 3 1152 254 0 129 6 285 7 139 6 63 3 MOMENT KG CM IN LBS 792 688 1584 1375 2333 2025 3082 2675 3830 3325 4579 3975 5328 4625 6077 5275 6825 5928
189. y 2006 Pilot s Operating Handbook E Section 919 XTRA BECKER ATC 4401 Transponder EXTRA 300 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 919 1 4 FLIGHT OPERATION IN MODE A TRANSPONDER REPLY CODE ONLY 919 1 5 919 1 6 919 1 7 1 2 Select squawk as described above Set mode switch A from SBY to ON The transponder immediality replies with the set code A triangle on the left next to the code signals the tranponder replies FLIGHT OPERATION IN MODE A C REPLY CODE AND ALTITUDE CODE 1 Select squawk as described above 2 ATC requests the transmission alpha charlie or charlie switch the transponder to ALT using mode switch A 3 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 c
190. y are shining If the display presents the Total Extreme Value you will see A 9 0g 5 09 on the 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 00 ABSOLUTE EXTREME VALUES C Two further extreme acceleration values are the positive and the negative Absolute Ex treme 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 Addi tionally 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 Extreme Values is signed by 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 c

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