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1. 912 3 Front Panel 912 3 System E 912 5 Error Reporting Fault 912 7 EIMINTANONS 912 8 EMERGENCY PROCEDURES 912 8 NORMAL PROCEDURES 912 8 azizell bee 912 8 Page Date 31 January 2006 912 1 Section 912 mE Pilot s Operating Handbook FILSER TRT 600 Transponder XTRA EXTRA 300S Left blank intentionally 912 2 Page Date 31 January 2006 Pilot s Operating Handbook E Section 912 EXTRA 3008 XTRA FILSER TRT 600 Transponder 912 1 GENERAL The TRT 600 is Level 2es Class2 SSR Mode S Elementary Surveillance Transponder It has Mode A Mode A C and Mode S capability In Mode S the transponder provides acquisition capability Furthermore the TRT 600 has a built in barometric pressure altitude coder in 100 ft increments NOTE Refer to latest edition of Filser TRT 600 Pilot s Operation Manual Doc No 03 200 010 11 to get familiar with the TRT 600 Transponder The following illustration of the front panel of the TRT 600 will assist the operator to understand this Mode S Transponder Display or sat On Off Flight Di FID Rotating krot for 1000 Rotating for 1 Sguitter flag elimina
2. 4 7 4 7 GCGRUISE 4 7 4 8 LANDING PROCEDURES 4 8 4 8 1 lt 4 8 4 8 2 c 4 8 4 8 3 Before STR EE 4 8 4 8 4 Normal Landing bate 4 8 4 9 GO AROUND e Hu 4 9 4 10 4 9 4 11 LEAVING THE AIRCRAFT 4 9 4 12 ACROBATIC 4 10 4 12 1 General 4 10 4 12 2 EAA 4 10 4 12 3 Sppe 4 12 Page Date 31 January 2006 4 1 Section 4 Normal Procedures XTRA Pilot s Operating Handbook EXTRA 300S Left blank intentionally Page Date 20 April 2002 Pilot s Operating Handbook Section 4 EXTRA 300S X TRA Normal Procedures SECTION 4 NORMAL PROCEDURE 4 0 GENERAL 4 0 1 AIRSPEEDS FOR NORMAL OPERATION SPEEDS IN KIAS CATEGORY ACRO NORMAL Start Rotating Speed 60 65 Climb Vx 87 93 Vy 96 104 Recommended Normal Climb Speed 100 110 Max Cruise Speed 18
3. 918 5 EMERGENCY PROCEDURES cec rire reote cei utere 918 5 Important COd S TE 918 5 NORMALPROCEDURES 2 aaa aanaeio 918 6 anaa eae 918 6 Page Date 31 January 2006 918 1 Section 918 mE Pilot s Operating Handbook BECKER ATC 2000 Transponder XTRA EXTRA 3005 Left blank intentionally 918 2 Page Date 31 January 2006 Pilot s Operating Handbook 2 Section 918 EXTRA 300S XTRA BECKER ATC 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 C Fourth digit D M Coding switch Mode switch Coding switch Controls Description Function OFF SBY ON ALT TEST F
4. 60 80 100 120 140 160 180 200 CAS CALIBRATED AIRSPEED kts NOTE Indicated airspeed assumes zero instrument error Page Date 20 April 2002 Pilot s Operating Handbook Section 5 EXTRA 300S XTRA Performance 5 4 STALL SPEED CONDITION POWER IDLE FORWARD C G STALL SPEEDS ANGLE OF BANK WEIGHT CATEGORY 0 30 45 1g 1 15g 1 419 920 NORMAL KIAS KIAS KIAS 2028 Ibs 59 64 70 820 kg ACRO KIAS KIAS KIAS 1808 Ibs 55 59 65 Max altitude loss during stall recovery is approximately 100 ft Page Date 20 April 2002 Section 5 Pilot s Operating Handbook Performance XTRA EXTRA 300S 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 C 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 920 65 SL 96 315 207 679 115 377 248 813 133 436 285 935 2028 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
5. 916 5 Page Date 31 January 2006 916 1 Section 916 mE Pilot s Operating Handbook BENDIX KING KT 76A Transponder XTRA EXTRA 3005 Left blank intentionally 916 2 Page Date 31 January 2006 Pilot s Operating Handbook 7 Section 916 EXTRA 3005 XTRA BENDIX KING KT 76A Transponder 916 1 GENERAL The BENDIX KING KT 76A panel mounted transponder receives interrogations at 1030 MHz and these trigger a coded response of radar pulses which are transmitted back to ATC at 1090 MHz The return reinforces your aircrafts image or blip on the controller s radar screen The KT 76A can reply to radar in any of 4096 preselected codes Each code is identified by a unique group of pulses With either an separate encoder the KT 76A also provides ground radar with 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 a
6. 6 p Long Range Wing Tank Capacity eene nnne nnne 6 p pig HOOK quc 8 p Simokesysteim EE CC II 6 p Reserved Reserved Reserved FILSER 600 8 FILSER 800 8 GARMIN GTX 327 6 p GARMIN GTX 330 8 p BENDIX KING KT 76A Transponder eese nennen nnne 6 p BENDIX KING KT 73 Transponder 2 8 BECKER 2000 Transponder 6 p BECKER 4401 Transponder 2 essen enne nennen nannten 8 p BECKER 6401 Transponder 10 p Page Date 31 January 2006 Section 9 Pilot s Operating Handbook Supplements XTRA EA 300S Left blank intentionally 9 2 Page Date 20 April 2002 Pilot s Operating Handbook Section 9 EA 300S XTRA Supplements 9 SUPPLEMENTS 9 1 INTRODUCTION Section 9 Supplements of the Pilot s Operating Handbook contains all information neces sary for a sa
7. 20 April 2002 Pode 20 April 2002 oro 31 January 2006 Vc 31 January 2006 QA 20 April 2002 7 Athru 7 7 20 April 2002 0 5 thru 0 6 20 September 2006 7 8thru 7 12 31 January 2006 iid dicatnr 31 January 2006 7 13thru 7 14 20 April 2002 pp 20 April 2002 8 1 thru 8 4 20 April 2002 1 3thru 1 5 31 January 2006 31 January 2006 1 6thru 1 8 assesses 20 April 2002 c2 NR TW 20 April 2002 31 January 2006 E 31 January 2006 2 2thru 2 3 20 April 2002 4 E A 20 April 2002 2 4thru 2 6 31 January 2006 901 1 thru 901 4 20 April 2002 P 20 September 2006 902 1 thru 902 4 20 April 2002 31 January 2006 903 1 thru 903 10 20 April 2002 9 20 September2006 904 1 thru 904 2 20 April 2002 31 January 2006 904 3 thru 904 4 31 January 2006 QA 20 April 2002 904 5thru 904 6 20 April 2002 lt 20 September2006 905 1 thru 905 6 20 April 2002 31 January 2006 906 1 thru 906 6 20 April 2002
8. 2 5 2 7 1 Normal Fig 2 5 2 7 2 j C 2 5 2 8 ACROBATIC 2 5 2 8 1 Were 2 5 2 8 2 Em 2 6 2 9 LOAD p 2 7 2 9 1 EE 2 7 2 9 2 Pig 2 7 2 10 KINDS OF OPERATIONAL LIMITS 2 7 2 11 STRUCTUAL TEMPERATURE COLOUR LIMITATION 2 7 2 12 MAXIMUM OPERATING 2 7 2 13 TIRE PRESSURE pem c 2 7 2 14 MARKINGS AND PLACARDS 2 7 2 14 1 Aircraft Identity Deut thee god ee eg tpe Ea Deut Fue 2 7 2 14 2 Operating PlaCAnS ce 2 8 2 14 3 Instrument rne 2 11 2 15 KINDS OF OPERATION EQUIPMENT 2 12 2 16 NOISE LEVEL Ee 2 13 Section 2 Pilot s Operating Handbook Limitations XTRA EXTRA 3005 Left blank intentionally 2 2 Page Date 20 April 2002 Pilot s Operating Handbook Section 2 EXTRA 300S XTRA Limitations SECTION 2 LIMITATIONS 2 1 GENERAL This section includes operating limitations instrument markings and basic placards necessary for the safe operation
9. 918 1 3 MODE A OPERATION 1 Activate the transponder on ATC request only To enshure instant readiness position the mode switch to SBY standby during the flight Set the code requested by ATC using the four coding switches Set two digit code numbers in the first two windows of the readout Caution Only operate the coding switches in the SBY standby mode 3 Switch the mode switch ON on ATC request the transponder then responding to mode A interrogation with dialed code as indicated by the REPLY lamp coming on Only press the IDENT button briefly when requested by ATC causing a special identification pulse SPI pulse being transmitted permitting instant identification of the aircraft on the ATC radar system 918 1 4 MODE A AND C OPERATION 918 2 918 3 918 3 1 1 Postion mode switch to ALT on ATC request only The transponder then responds with dialed code causing REPLY lamp to light up and additionally transmits the height of the aircraft to ATC 2 Press the IDENT button briefly when requested by 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 M
10. 6 Maximum air towing speed 2 maximum permissible air towing speed of the glider 7 The maximum permissible cylinder head temperature is 500 F red line 8 interior mirror mounted For the location of the yellow release knob the following placard has to be attached in the near of the knob AIR TOW Page Date 20 April 2002 907 3 XTRA rete on 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 RELEASE 3 Landing PERFORM AS PRACTICAL D TOW BREAK 1 Pilot of the glider INFORM 2 Landing PERFORM AS PRACTICAL NORMAL PROCEDURES Preflight inspection starting procedures take off procedure and the following climbing flight have to be carry out in accordance with Chapter 4 Normal procedure In addition to this procedures the following points have to be observed A PRIOR TO THE TAKE OFF A release test needs to be conducted to determine safe release operation The test shall be made on both aircraft and glider B TAKE OFF After air tow h
11. 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 with Mode A C only You will need to consult an authorized service station to enter the ICAO aircraft address see TRT 600 Installation Manual Please consult your airworthiness authority for national procedures NOTE If no valid ICAO 24 bit aircraft address is programmed to the unit or if the memory is inoperative the transponder will inhibit the Mode S functions In this case only Mode A C function will be available 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 31 January 2006 Pilot s Operating Handbook TR A EXTR
12. Page Date 31 January 2006 1 5 Section 1 General XTRA T 1 7 OIL Continuation Average ambient air Mil L6082 Mil 22851 temperature grades ashless dispersant grades 18 C til 21 C SAE 30 SAE 30 40 or 20W40 70 F 18 C til 32 C SAE 20W50 SAE 20W50 or 15W50 90 F lt 12 10 F SAE 20 SAE 30 or 20W30 single or multi 1 8 LOADING Wing loading Power loading 1 9 TERMINOLOGY Air Speeds CAS KCAS GS IAS KIAS TAS VA VNE VNO VS VX viscosity aviation grade oils see latest issue of Textron Lyc 5 1 No 1014 88 1 kg m Normal 78 5 kg m Acrobatic 3 07 kg hp Normal 2 73 kg hp Acrobatic Calibrated Air Speed CAS is the same as TAS True Air Speed in std atmospheric condition at sea level Calibrated speed in knots Ground speed Indicated air speed Indicated speed in knots True air speed It s the same as CAS compensated for altitude temperature and density Maneuvering speed Never exceed speed Maximum structural crusing speed Stalling speed or minimum steady flight speed Best angle of climb speed Best rate of climb speed Page Date 20 April 2002 Pilot s Operating Handbook Section 1 EXTRA 300S 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 inch inch
13. 0276 661 o 0 1 056 006 058 008 0SL 007 ee HLI 22028191 v1 2101 9 p OL 1913 5417081 SH 602 9666 81 vS9L 125 SN 9111 np vv uiu WSI 0008 lt YSI 0002 S81 481 098 OL 1304 OL SINIL LTV LH9I3M VSI 033dS LV g8INI1O H3MOd LNOO 02 SNOILIGNOO re OL AWIL Page Date 20 April 2002 5 10 Section 5 Performance Pilot s Operating Handbook EXTRA 300S XTRA RANGE AND ENDURANCE 5 8 2 SYH S V WN 009 005 007 0002 000 0009 0008 008 ooz 00001 0002 000v 00091 SNOLLIQNOO YSI AGNLILIW 9NISIQHO OL H3MOd 1 XVIN ANY 15 WWD sn lt 0 112 175 SN 55 411 IZ sn 4179 WD SN HLT 1 1 597 8202 9M 026 WLOL LHOIEM O L NOLLIQNOO 1333 SHH 2 Sip 0008 9H S lZ 2dM OSEZ WdY 7S9 118 3511439 9 11135 uaMOd 0002 000 0009 0008 00001 00021 000v 00091 1333 5 11 Page Date 20 April 2002 Section 5 2 Pilot s Operating Handbook Performance E
14. 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 31 January 2006 912 3 Section 912 Pilot s Operating Handbook FILSER TRT 600 Transponder XTRA EXTRA 300S 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 BUTTONS ON OFF The unit can be turned on by pressing the ON OFF button for less then 1 second The unit can be turned off by pressing the ON OFF button for more then 2 seconds also refer to the System Operation Paragraph 912 1 2 MODE The following modes can be selected in sequence by pressing the MODE button STBY Standby Mode used for aircraft on ground with reduced squitter rate only Mode S with altitude reporting all ZERO only 5 A active with Mode C frames only and Mode S with altitude reporting all ZERO only ACS Mode and 5 full active ARROWS UP AND DOWN To activate the inserted SQUAWK CODE fromthe lower standby line to the upper active position the button with the UP AND DOWN ARROWS shall be pressed
15. 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 3005 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 aaiae aaia 5 3 Performance aa eaaa a ran eut nar edd AEEA 5 3 crea 5 3 Sample 5 3 ISA CONVERSION 5 5 AIRSPEED CALIBRATION 5 6 STALL SPEED pe cm 5 7 TAKE OFF 4 4200 5 8 RATE OF CLIMB PERFORMANCE 5 9 TIME TO CLIMB FUEL TO CLIMB 5 10 RANGEAND ENDURANCE causa cane F Rana yam anas nada 5 11 22 5 12 CRUISE PEHFORMANDGE riconosce enean 5 13 LANDING PERFORMANCE 2 224444 44 5 14 Page Date 20
16. USE OF HEADSET IS REQUIRED on the right side of USE OF PARACHUTE IS RECOMMENDED instrument panel LOW RPM lt PROP gt on RPM control unit in the rear cockpit lt MIXTURE gt on mixture control unit in the rear cockpit CLOSE lt THROTTLE gt nearthrottle control in both cockpits CANOPY LOCLK LOCK lt gt UNLOCK lt gt LOCK near canopy locking handles of each cockpit near the eyeball type adjustable vents OPEN CAUTION Particular caution must be exercised when performing A in cockpit maneuvers at speeds above Va 158 KIAS Large or abrupt control inputs above this speed may impose un acceptably high loads which exceed structural capability of the aircraft Page Date 20 September 2006 2 9 Section 2 Limitations XTRA Pilot s Operating Handbook EXTRA 3005 APPROVED ACROBATIC MANEUVERS AND RECOMMENDED ENTRY AIRSPEEDS Maneuvers Segment horizontal Line 45 climbing 90 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 NO BAGGAGE speeds min KIAS max KIAS in cockpit on Lexan cover aft pilot s seat if installed 2 10 Page Date 31 January 2006 Pilot s Operating H
17. 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 interrogations the letter R is displayed on the left top side of the display 912 4 Page Date 31 January 2006 Pilot s Operating Handbook E Section 912 EXTRA 3005 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 en
18. NORMAL ACROBATIC COMMUNICATION 1 Transceiver VHF 1 1 ELECTRICAL POWER 1 Battery 1 1 2 Alternator 1 1 3 Ampermeter 1 1 FLIGHT CONTROL SYSTEM 1 Elevator trim control 1 1 2 Stall warner 1 1 FUEL 1 Boost pump 1 1 2 Fuel quantity indicator 2 2 3 Manifold pressure 1 1 4 Fuel flow indicator 1 1 5 Fuel pressure 0 0 LIGHT 1 Wing tip position strobe light 1 1 NAVIGATION 1 Altimeter 1 1 2 Airspeed indicator 1 1 3 Mag direction indicator 1 1 4 OAT indicator 0 0 5 Vertical speed indicator 0 0 6 Turn amp bank indicator 0 0 2 12 Page Date 20 September 2006 EXTRA 3005 Pilot s Operating Handbook Section 2 XTRA Limitations NORMAL ACROBATIC 7 Artificial horizon 0 8 Directional gyro 0 0 9 Transponder 1 ENGINE CONTROL 1 RPM indicator 1 1 2 Exhaust gas temperature ind 0 0 3 Oylinder head temperature ind 0 0 OIL 1 Oil temperature indicator 1 1 2 Oil pressure indicator 1 1 FLIGHT CREW EQUIPMENT 1 Parachute 0 2 Seat belt 1 1 3 Headset 1 1 NOTE The zeros 0 used in the above list mean that either the equipment or system or both were not required for type certification for that kind of operation Either equipment or systems in addition to those listed above may be required by the national operating regulations The asterisk used in the above list means that latest national aviation regulations must
19. Page Date 31 January 2006 7 11 Section 7 Pilot s Operating Handbook EXTRA 300S XTRA Description and Operation of Aircraft and Systems E 3 5 11 3 0815 120 6 3 yT e01r6 v3 20166 93 207 6 93 20166 93 DNIA H1 111 34041 DNIA snfpy Yopad dWnd 150089 gt 0 aa 2 44048 016 3 sna NIVW AIuo 1ueuudinbz3 5 0 20166 3 6 201 6 V3 Page Date 31 January 2006 15232 Pilot s Operating Handbook Section 7 EXTRA 300S X TRA Description and Operation of Aircraft and Systems 7 13 CABIN ENVIRONMENT CONTROL A ventilation system in the canopy is provided for the supply of fresh air to the cabin The bad weather window is equipped with a ventilation scoop to provide supply of fresh air to the cabin Additionally to the left and right of the cockpit eyeball type adjustable vents are installed Page Date 20 April 2002 7 13 Section 7 Pilot s Operating Handbook Description and Operation of Aircraft and Systems XTRA EXTRA 300S Left blank intentionally 7 14 Page Date 20 April 2002 gea XTRA SECTION 8 HANDLING SERVICING AND MAINTENANCE Table of Contents Paragraph Page 8 1 ll ggiejsjeie m 8 3 8 2
20. 2 4 Page Date 31 January 2006 Pilot s Operating Handbook Section 2 EXTRA 300S XTRA Limitations f Cylinder head temperature Max 500 F 2 5 PROPELLER MT Propeller Entwicklung GmbH Federal Republic of Germany a Type MTV 9 B C C 200 15 b Type MTV 14 B C C 190 17 Max Take Off max 5 min 2700 RPM Max Continuous 2400 RPM NOTE If not stated otherwise refer to section 4 12 Acrobatic Maneuvers the aircraft may be operated in acrobatic maneuvers up to 2700 RPM 2 6 WEIGHT LIMITS Max allowed empty weight Normal category 711 kg 1567 165 Acrobatic category 697 kg 1536 Ibs Max allowed T O weight Normal category 920 kg 2028 Ibs Acrobatic category 820 kg 1808 Ibs Max allowed landing weight 920 kg 2028 Ibs 2 7 WEIGHT AND C G ENVELOPE Vertical reference fire wall Horizontal reference upper longerons in cockpit 2 7 1 NORMAL FLIGHT Max T O Weight forward C G rear C G 920 kg 2028 Ibs 48 9 cm 19 3 71 4 cm 28 1 and below 2 7 2 ACROBATIC FLIGHT Max T O weight forward C G rear C G 820 kg 1808 165 48 9 cm 19 3 71 4 cm 28 1 and below 2 8 ACROBATIC MANEUVERS 2 8 1 NORMAL FLIGHT All acrobatic maneuvers are prohibited except stall chandelle lazy eight and turns up to 60 degrees bank angle Page Date 31 January 2006 2 5 Section 2 2 Pilot s Operating Handbook Limitations XTRA EXTRA 3005 2 8 2 ACROBATIC FLIGHT
21. Current Extreme Value or if they are reset to Og Here is an example Since the last reset of the Current Extreme Values and the Total Extreme Values the maximum of the positive acceleration was 9g and the maximum of the negative acceleration was 5g The Instantaneous Acceleration is 3g Therefore the middle LED and the first three positive LEDs are illuminated for the Instantaneous Accel eration Furthermore the ninth LED in positive direction is illuminated for the positive Cur rent Extreme Value and the fifth LED in negative direction for the negative Current Ex treme Value The LC Display shows 9 09 A 50g 902 4 Page Date 20 April 2002 Pilot s Operating Handbook Z Section 902 EXTRA 300S X TRA Electronic Accelerometer After resetting the Current Extreme Values the LC Display shows A 3 0g 0 00 and only the middle LED and three LEDs the positive range of the LED Display are shining If the display presents the Total Extreme Value you will see A 9 0g 5 00 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 0g 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 th
22. INFORMATION MANUAL EXTRA 3005 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 XTRA EXTRA 300S 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 2 1 3 EMERGENCY PROCEDURES issiaiskinti Po unde baden o a sd dac na nu 3 1 4 NORMAL PROCEDURES ertt egent ctetur re er qae 4 1 b PERFORMANCE secerneren ras entree nU RR ERR ERA 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 XTRA nir THIS HANDBOOK SHALL ALWAYS BE CARRIED ON BOARD DURING FLIGHT PILOTS OPERATING HANDBOOK PREPARED THIS MANU
23. NAV COM Garmin GNS 430 2 95 1 21 1 Transponder Bendix King KT 73 1 64 1 21 1 Transponder Bendix King KT 76A 0 89 1 21 1 Transponder Filser TRT 600 LAST 0 70 1 26 1 Transponder Filser TRT 800 0 70 1 26 1 Transponder Garmin GTX 327 0 95 1 21 1 Transponder Garmin GTX 330 1 50 1 21 1 Transponder Becker BXP6401 1 0 80 1 26 1 Transponder Becker BXP6401 2 0 80 1 26 1 Transponder Becker ATC 2000 1 20 1 21 1 Transponder Becker ATC 4401 0 73 1 26 1 Transponder Antenna Comant Industries 105 0 11 0 12 1 Transponder Antenna Bendix King KA 60 0 11 0 12 1 Moba 210FA 0 10 4 07 R 1 COM Antenna Extra 83205A 0 10 4 07 A 1 COM Antenna Pointer P1 3001 10 0 05 4 07 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 17 R 1 Battery Concorde RG 25XC 10 40 0 17 A 1 Batt Charger Plug EXTRA 146 19 20 0 02 0 12 1 External Power Recept Div AN2552 3A 1 46 0 76 1 Ext Power Solenoid Switches Kidde 22735 0 40 0 02 1 Ext Power Solenoid White Rodgers
24. Pilot s Operating Handbook Section 903 EXTRA 300S X TRA Emergency Locator Transmitter 903 EMERGENCY LOCATOR TRANSMITTER 903 1 GENERAL To improve the passive security the EXTRA 300 S 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 903 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 high of the ELT unit placard above the ELT circuit breaker see Fig 1 REMOTE SWITCH 00000000000 CIRCUIT BREAKER 1A Figure 1 Page Date 20 April 2002 903 3 Section 903 iom Pilot s Operating Handbook Emergency Locator Transmitter X TRA EXTRA 300S 903 3 EMERGENCY PROCEDURES Aircraft accident or forced landing A Manual activation Warbling tone heatset 121 5 MHz Broken or disabled antenna Severed whip antenna cable Danger of fire in aircraft Temperature extreme in aircraft Poor transmitting location Short circuit in A C electric ves D Removal of ELT from A C 9 Pay attention for best E transmission cond
25. 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 300S XTRA Publication Guidance 4 LOG OF EFFECTIVE PAGES Dates of issue for original and revised pages Date and sign of approval are 13 March 1993 LBA approved 19 March 1993 Revision No 1 6 October 1994 LBA approved 24 January 1995 Revision No 2 26 June 1997 LBA approved 27 August 1997 Edition N92 tt 20 April 2002 LBA approved 30 October 2002 Rev No 1 2nd Ed 31 January 2006 EASA Approval EASA A A 01169 Date of Approval 8 March 2006 Rev No 2 2nd Ed 20 September 2006 EASA Approval EASA A A 01319 Date of Approval 20 November 2006 Page Date 20 September 2006 0 5 ion Pilot s Operating Handbook Guidance X TRA EXTRA 300S LOG OF EFFECTIVE PAGES cont Page Date Page Date TNS auca 31 January 2006 6 12thru 6 13 20 September 2006 E RE 20 April 2002 6 14 ss ete tse 31 January 2006 31 January 2006 uel AE 31 January 2006 0 1 thru 0 2
26. 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 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 31 January 2006 Pilot s Operating Handbook 7 Section 918 XTRA BECKER ATC 2000 Transponder EXTRA 300S
27. s Operating Handbook Section 915 EXTRA 300S 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 31 January 2006 915 7 Section 915 mE Pilot s Operating Handbook GARMIN GTX 330 Transponder XTRA EXTRA 3005 Left blank intentionally 915 8 Page Date 31 January 2006 Pilot s Operating Handbook TR A EXTRA 300S Paragraph 916 1 916 1 1 916 1 2 916 1 3 916 2 916 3 916 4 916 4 1 916 5 SECTION 916 BENDIX KING KT 76A TRANSPONDER Table of Contents Page GENERAL 916 3 Code SSIS CUON 916 3 GIJN mE 916 4 Testing the AGA Accuses tens eer d cede c 916 4 LIMITATIONS cS 916 4 EMERGENCY PROCEDURE 916 4 NORMAL PROCEDURE cerae trente nuns sesecceesexesueesetecseecueeeesesceess 916 5 916 5 PERFORMANCE inci viscose
28. 12 MANUFACTURER Manufacturer EXTRA Flugzeugproduktions und Vertriebs GmbH Flugplatz Dinslaken 46569 H nxe Federal Republic of Germany 1 3 TECHNICALDATA 1 3 1 3 View Drawing lt Page Date 31 January 2006 1 3 Section 1 General XTRA Pilot s Operating Handbook EXTRA 300S 1 3 2 Main Data Length Height Span Wheel base Wheel track 1 3 3 Wing Wing span Wing area Airfoil Chord MAC Aileron area Aileron deflection 1 3 4 Horizontal Tail Span Area Airfoil 1 3 5 Elevator Area Elevator deflection Trim tab deflection 1 3 6 Vertical Tail 6 65 m 21 82 ft 2 62 m 8 60 ft 7 50 m 24 61 ft 1 80 m 5 91 ft 4 75 m 15 58 ft 7 5 m 24 61 ft 10 44 m 112 38 ft Root MA 15 S Tip MA 12 S Root 1 85 m 6 07 ft Tip 0 93 m 3 05 ft 1 44 m 4 72 ft 2 x 0 830 m 2 x 8 93 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 26 down 26 tolerance 2 157 tolerance 2 Area 1 39 m 14 96 ft Airfoil Wortmann FX 71 L 150 30 1 3 7 Rudder Area 0 51 m 5 49 ft Rudder deflection left 30 right 30 tolerance 2 1 4 Page Date 31 January 2006 Pilot s Operating Handbook Section 1 X TRA General EXTRA 3005 1 4 1 5 ENGINE Manufac
29. 300S Left blank intentionally 9 4 Page Date 20 April 2002 Pilot s Operating Handbook XTR A EXTRA 3005 Paragraph 901 1 901 2 901 3 901 4 901 5 901 6 901 7 901 8 SECTION 901 STEERABLE TAIL WHEEL Table of Contents Page GENERAL 901 3 LIMITATIONS Aaaa aa aa Aaaa 901 3 5 22224 0 oe HE nana mido arra 901 3 NORMAL PROCEDURES anat hann ch senseacdneataceunedsann cesnensaunesedcessaevnentse 901 3 udzehiiie 901 3 WEIGHT AND BALANCE 5 enint apos ea cad onn organ n 901 3 DESCRIPTION OF THE SYSTEM 2 901 3 HANDLING SERVICING AND MAINTENANCE 22 444422211 1 1 901 4 Page Date 20 April 2002 901 1 Section 901 Z Pilot s Operating Handbook Steerable Tail Wheel XTRA EXTRA 3005 Left blank intentionally 901 2 Page Date 20 April 2002 Pilot s Operating Handbook Section 901 EXTRA 300S Steerable Tail Wheel 901 901 1 901 2 901 3 901 4 901 5 901 6 901 7 STEERABLE TAIL WHEEL GENERAL To improve taxi and h
30. 31 January 2006 Pilot s Operating Handbook 2 Section 915 EXTRA 300S XTRA GARMIN GTX 330 Transponder Avoid selecting code 7500 and all codes in the 7600 7777 range These trigger special indicators in automated facilities Only the code 7500 will be decoded as the hijack code An aircraft s transponder code if available is utilized to enhance the tracking capabilities of the ATC facility therefore care should be taken when making routine code changes 915 1 3 KEYS FOR OTHER GTX 330 FUNCTIONS IDENT Pressing the IDENT key activates the Special Position Identification SPI Pulse for 18 seconds identifying your transponder return from others on the air traffic controller s screen The word IDENT will appear in the upper left corner of the display while the IDENT mode is active VFR Pressing the VFR key sets the transponder code to the pre programmed VFR code selected in the Configuration Mode Pressing the VFR key again will restore the previous identification code FUNC Pressing the FUNC key changes the page shown on the right side of the display Displayed data includes Pressure Altitude Flight Time Count Up timer Count Down timers In the Configuration Mode steps through function pages START STOP Starts and stops the Count Up Count Down and flight timers In the Configuration Mode steps through functions in reverse CRSR Initiates starting time entry for the Count Down timer andcancels transponder co
31. 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 1138 Page Date 20 April 2002 Section 5 Performance Pilot s Operating Handbook EXTRA 3005 XTRA lt RATE OF CLIMB PERFORMANCE 5 6 A Sql 991 7 81 9861 S602 204 201 30l 202 ose 008 0S8 006 0S6 USI USI USI USI USI 0 Es 3200091 2 e 3300081 008 4 99 3200021 v 3300001 oe es 140008 0091 3140009 8 33000 0002 01 30002 00 2 15 21 0082 vi 002 0261 uiui J 0262 DOH vs u0008 5 000Z Vd 481 94098 LHOI3M 31dWVX3 J0u Page Date 20 April 2002 Section 5 EXTRA 300S Pilot s Operating Handbook XTRA Performance TIME TO CLIMB FUEL TO CLIMB 5 7 1995
32. April 2002 524 Section 5 Pilot s Operating Handbook Performance lt 3008 blank intentionally 5 2 Page Date 20 April 2002 Pilot s Operating Handbook Section 5 EXTRA 300S XTRA Performance SECTION 5 PERFORMANCE 5 1 GENERAL Performance data charts on the following pages are presented to facilitate the planning of flights in detail and with reasonable accuracy under various conditions The data in the charts have been computed from actual flight tests with the aircraft and engine in good condition and using average piloting techniques It should be noted that the performance information presented in the range and endurance charts allow for 45 minutes reserve fuel at specified speeds Some indeterminate variables such as engine and propeller air turbulence and others may account for variations as high as 10 or more in range and endurance Therefore it is important to utilize all available information to estimate the fuel required for the particular flight 5 1 1 Performance Charts Performance data are presented in tabular or graphical form to illustrate the effect of diffe rent 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 g
33. alpha charlie or charlie switch the transponder to ALT using mode switch A 3 The transponder replies using the code set and in response to mode C requests it tansmits the flight level of the aircraft to ATC A triangle on the left next to the code signals the transponder replies SQUAWK IDENT After a squawk ident request from ATC press Ident button IDT D briefly This transmits an additional special pulse SPI for approx 18 seconds which enables the aircraft to be clearly identified on the radar screen of the controller Idt appears in the bottom line of the LC display during this time TEST The following different tests are integrated in the transponder or can be triggered at the transponder Automatic switching on test in which the display E is flashing with all digits for 3 seconds The unit is subject to a self test in this time A permanent test runs in the background of the transponder operation The built in FPGA organizes the required resources for this The transmitter recognizes a missmatching or own abnormal behavior and delivers an alarm signal to the FPGA Page Date 31 January 2006 919 7 Section 919 Pilot s Operating Handbook BECKER ATC 4401 Transponder XTRA EXTRA 3005 3 Afurther test of the unit is triggered if the VFR1 button F and VFR2 button G are pressed simultaneously At this test all segments must flash into display E as long as the buttons are pushed Add
34. constant speed propeller type MTV 14 B C C190 17 with a diameter of 1 9 m or optional with a 3 blade propeller type MTV 9 B C C200 15 with a diameter 2 0 THROTTLE Control lever cub type mounted on the left side in cockpit MIXTURE Vernier control located at right side of cockpit red knob RPM CONTROL Vernier control located at left side of cockpit blue knob Push pull type with friction lock on the left side of the rear cockpit Preselection of RPM possible due to constant speed governor Page Date 31 January 2006 7 9 Section 7 Nei Pilot s Operating Handbook Description and Operation of Aircraft and Systems X TRA EXTRA 300S 7 10 8 FUEL SELECTOR VALVE A rotary fuel selector valve is mounted behind the firewall on the right side of the fuselage A torque tube connects the valve to the cockpit handle Pull and turn the handle 90 to open the valve to the Acro amp Center tank A further 90 turn switches to the Wing tank fuel supply Position down CLOSED Position left ACRO amp CENTER TANK Position up WING TANK 7 10 9 EXHAUST SYSTEMS OPTIONAL Optionally the EA 300 S can be equipped with an additional silencer system type Gomolzig The attachment is integrated in the fuselage structure Thus no modifications are necessary to install the silencer system Alternatively a complete 6 in 1 System with integrated silencer is available 7 11 FUEL SYSTEM The fuel system consists of two se
35. it is recommended to use the same procedure as outlined for cold engine start 4 4 TAXIING THE AIRCRAFT 1 2 3 NO Canopy CLOSE AND LOCK Brake CHECK Altimeter Set on QFE or QNH Scale error max 60 ft Avionic master switch ON Electrical equipment ON Radio Set and test 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 Page Date 20 April 2002 Pilot s Operating Handbook Section 4 EXTRA 300S lt X TRA Normal Procedures 4 5 TAKE OFF PROCEDURE 4 5 1 BEFORE TAKE OFF Before you line up at the runway for take off Check oil pressure and oil temperature Check the magnetos 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 gauche 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 KIAS A light pressure on the stick lifts the tail to horizontal position
36. 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 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 31 January 2006 Pilot s Operating Handbook 7 Section 920 EXTRA 3005 XTRA BECKER ATC 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 sev
37. 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 2200 23 7 65 195 50 5 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 and Endurance 1 196 for each 10 C above below Standard Day Temperature for particular altitude 2 Leaning with exhaust gas temperature EGT gage For the adjustment Best Power first lean the mixture to achieve the top exhaust temperature peak and then enrich again until the exhaust temperature is 100 lower than peak EGT For the adjustment Best Economy s
38. 4 9 Section 4 Pilot s Operating Handbook Normal Procedures EXTRA 3005 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 This fact must be considered when pulling or pushing high g s 4 12 2 MANEUVERS CAUTION Particular caution must be exercised when performing maneuvers at speeds above 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
39. 5 1 No 1070 Total fuel capacity 171 liters 45 1 US Gallon Usable fuel capacity 169 liters 44 6 US Gallon For acrobatic flight wing tanks must be empty Total fuel capacity for acrobatic 51 liters 13 4 US Gallon in acro tank Usable fuel capacity for acrobatic 49 liters 12 9 US Gallon 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 acrobatic maneuvers up to 2700 RPM b Oil temperature gauge Max 245 F C Oil capacity Maximum sump capacity 16 qts Minimum sump capacity Acrobatic 12 qts Normal 9 qts d Cil pressure Minimum ldling 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
40. 70 111 225 5 0 40 0 02 cont operation 6 12 Page Date 20 September 2006 Pilot s Operating Handbook XTRA Section 6 EXTRA 300S Weight and Balance and Equipment List QTY ITEM MANUFACT PART OR P N WEIGHT REQUIRED R KG m INSTALLED OPTIONAL O ALTERNAT A 1 Main Bus Solenoid White Rodgers 70 111 226 5 0 40 0 02 R 1 Starter Solenoid Switches Kidde 22735 0 40 0 02 R 1 Low Voltage Light OAK MS25041 2 0 02 1 31 R 1 Ignition TCM 10 357200 1 0 15 1 30 R Switch 2 Wheel Cleveland 40 151 4 00 0 16 R 2 Main Wheel Tires Div 5 00 5 6PR 3 90 0 16 R 1 Tail Wheel 5 EXTRA steerable 5 50 4 91 A 1 Tail Wheel 5 EXTRA free swivel type 5 50 4 91 R 1 Tail Wheel 6 Assy Special Products 5 90 4 91 A Soft Aviation Inc 2 Brake Assy Cleveland 30 164 1 40 0 16 R 2 Brake Cyl Cleveland 10 20 or 10 20E 0 55 0 89 R 2 Brake Cyl Matco MC 4E 0 55 0 89 A 1 Brake Fluid Reservoir EXTRA 53301 1 0 20 0 03 R 1 Brake Fluid Reservoir ACS A 315 0 20 0 04 A 1 Safety Belt Hooker 1011 230 3 30 1 95 R Assy with ratchet 2 NAV STROBE LTS Whelen A 600 PG PR 14 0 23 0 56 R 2 Power Supply Whelen A490T 0 54 0 56 2 Electric Actuator SKF CARR 3 25 0 65 Pedal Adjust 22x200x1 D12B 1 Long Range Tank EXTRA 84901 1 80 0 38 1 Fuel Selector Spruce 108HD 04 0 30 0 56 R 1 Fuel Selector Allen 6S 122 0 19 0 56 A 1 Safety Cover EXTRA 84803 1 2 53 2 80 Polycarbonate 1 Dual Pump EXTRA 84100 6 4
41. 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 krot for 1000 Rotating 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 push buttons Page Date 31 January 2006 913 3 Section 913 Pilot s Operating Handbook FILSER TRT 800 Transponder XTRA EXTRA 300S 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 BUTTONS ON OFF The unit can be turned on by pressing the ON OFF button for less then 1 second The unit can be turned off by pressing the ON OFF button for more then 2 seconds also refer to the System Operation Paragraph 913 1 2 MODE The following modes can be selected in sequence by pressing the MODE button STBY Standby Mode used for aircraft on ground with reduced squitter rate only Mode S with altitude reporting all ZERO only 5 A a
42. 917 6 Page Date 31 January 2006 Pilot s Operating Handbook Section 917 EXTRA 300S 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 identification codes 917 4 NORMAL PROCEDURES Not applicable 917 5 PERFORMANCE Not applicable Page Date 31 January 2006 917 7 Section 917 mE Pilot s Operating Handbook BENDIX KING KT 76A Transponder XTRA EXTRA 3005 Left blank intentionally 917 8 Page Date 31 January 2006 Pilot s Operating Handbook TR A EXTRA 300S 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 918 3 TS 918 4 Squawk selection 918 4 Mode Operations 918 5 Mode A and C 918 5 LIMITATIONS
43. 920 9 Section 920 Pilot s Operating Handbook BECKER ATC 6401 Transponder XTRA EXTRA 3005 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 delivered the VFR button is not assigned a code This means that if this button is pressed for 0 5 seconds is shown in the code display and the transponder then switches back to the previously active code 920 1 10 CONFIGURATION MODE The configuration mode is available from SBY mode only To get into configuration mode press button SEL turn rotary encoder B until CFG appears in the bottom row of the display Refer to BECKER s Pilot s Guide for available options 920 2 LIMITATIONS Not applicable 920 3 EMERGENCY PROCEDURES 920 3 1 IMPORTANT CODES 7600 Loss of communications 7500 Hijacking 7700 Emergency All secondary surveillance radar sites are ready to receive this code at all times See the Airman s Information Manual AIM for a detailed explanation of identification codes 920 4 NORMAL PROCEDURES Not applicable 920 5 PERFORMANCE Not applicable 920 10 Page Date 31 January 2006
44. External Power XTRA EXTRA 3005 Left blank intentionally 904 6 Page Date 20 April 2002 XTRA SECTION 905 DIGITAL RPM INDICATOR Table of Contents Paragraph Page 905 1 GENERAL c 905 3 905 2 BI apgnenme 905 3 905 3 EMERGENCY PROCEDURES 905 3 905 4 NORMAL PROCEDURES anii 905 3 905 5 EM 905 4 905 6 WEIGHT AND BALANCE enean cns Ld aa Ene dum nad 905 4 905 7 DESCRIPTION OF THE SYSTEM nena 905 4 905 8 HANDLING SERVICING AND MAINTENANCE 4 2 44 22211 905 6 Page Date 20 April 2002 905 1 Section 905 Pilot s Operating Handbook Digital RPM Indicator XTRA EXTRA 300S Left blank intentionally 905 2 Page Date 20 April 2002 Pilot s Operating Handbook Section 905 XTRA Digital RPM Indicator EXTRA 3005 905 905 1 905 2 905 3 905 4 DIGITAL RPM INDICATOR GENERAL The EXTRA 300 S can be equipped with the optional P 1000 Digital RPM indicator alterna tiv to the mechanical VDO RPM indicator LIMITATIONS The operation limitations are not affected due to the installati
45. IS 58 7 CM 23 1 IN AFT OF REF DATUM MTOW ACRO EMPTY WEIGHT 45 0 500 550 600 65 0 700 ARM CM 197 217 236 256 27 6 INCH CENTER OF GRAVITY CM INCH AFT OF REF DATUM Page Date 20 April 2002 Section 6 Weight and Balance and Equipment List XTRA Pilot s Operating Handbook EXTRA 300S 6 6 EQUIPMENT LIST EXTRA 3005 S N QTY ITEM MANUFACT PART OR P N WEIGHT 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 80 Silencer GO3 606500 1 Exhaust System Gomolzig EA300 606000 8 20 0 39 A 6 in 1 with Silencer 1 Fuel Injector Bendix RSA 10 AD 1 3 90 0 68 R 1 El Fuel Pump Weldon Tool 8120 M or B8120 M 1 10 0 04 R 1 Oil Cooler Stewart Warner 8406 R 1 40 0 90 R 1 2 Oil Cooler Stewart Warner 8406 R 1 40 0 20 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
46. N WEIGHT MARK IF REQUIRED R KG m INSTALLED OPTIONAL ALTERNAT A 1 Governor Woodward A 210 988 1 10 0 91 R 1 Governor MT Propeller P 880 5 1 10 0 91 A 7 Switches Cutler Hammer div 0 28 1 31 R 7 Switches Kissling div 0 28 1 31 A 11 Circuit Breaker Potter amp Brumfield div 0 50 1 29 R 11 Circuit Breaker ETA or Klixon div 0 30 1 29 A Main Bus Fuseholder MTA 03 00360 0 03 0 02 Main Bus Strip Fuse 02 00300 40 Amps 1 PCB Auto Fuse EXTRA 83290 1 0 01 0 02 1 Fuel Cont Probe VDO 226 801 015001G 0 12 0 33 R Wing Tank 1 Fuel Cont Probe VDO 224 082 007 004R 0 19 0 68 R Center Tank 1 Fuel Cont Ind VDO 301 271 036 001 K 0 08 1 30 R Wing Tank or 301 030 001 G 1 Fuel Cont Ind VDO 301 272 052 001 K 0 14 1 30 R Acro Tank or 301 030 002 G 1 Ammeter VDO 190 004 039 002 0 08 1 31 R or 190 037 002 1 Volt Ammeter Electronics Intern VA 1A 0 26 1 30 A 1 Shunt Electronics Intern S 50 0 09 1 20 A 1 Volt Ammeter Electronics Intern VA 1A 50 0 22 1 30 A 1 RPM Indicator VDO 333 230 115 002 0 31 1 28 R or 333 035 001 G 1 RPM Indicator digital Horizon P100 230 643 00 0 68 1 28 A 1 Magn Dir Ind Airpath C 2300 0 25 1 30 R 1 Oil Press AMITEK or Christen 61943 0 51 1 30 R Oil Temp Ind 1 Oil Press Westach 3DA3 3MM 0 14 1 30 A Oil Temp Ind 3 1 8 or 3DA3 3KV 1 Oil Temp Sender Westach W399 S9 0 08 0 11 A 1 Oil Press Sensor Mediamate 387 100MM 0 12 0 04 A or 387 100KV 1 Oil Press Westach 2DA
47. Section 7 EXTRA 300S 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 S is designed and developed by EXTRA Flugzeugproduktions und Vertriebs GmbH 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 S is a light weight robust single piston engined one seat aircraft with a fuselage structure in tig welded steel tube construction The landing gear wing and tail are made of epoxy reinforced with glass and carbonfiber The items are qualified up to 72 C The standard aircraft is designed to operate within a range of ambient air temperature from 20 C to 44 C A F gt 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 kit 7 2 FUSELAGE The fuselage structure consists of a steel tube construction integrating the wing and empennage connections as well as the seat The lower front part of the fuselage and the sides below the wing are faired with aluminium sheet metal Within the exhaust area stainless steel sheet metal is used T
48. Tank 511 13 4 US Gallons Usable fuel capacity in the system 203 L 53 5 US Gallons For acrobatic flight wing tanks must be empty Usable fuel capacity for acrobatic 49 L 12 9 US Gallons WEIGHT LIMITS Max allowed empty weight Normal category 686 kg 1513165 PLACARD The existing FUEL SELECTORVAL VE placard has to be replaced by the following plac ard FUEL SELECTOR VALVE WING TANKS usable 154 L 40 7 US GAL on right aux spar hardpoint near selector valve handle ACRO amp CENTER TANK usable 49 0L 12 9 US GAL EMERGENCY PROCEDURES Not affected NORMAL PROCEDURES Not affected Page Date 20 April 2002 906 3 Section 906 iom Pilot s Operating Handbook Long Range Wing Tank Capacity XTRA EXTRA 300S 906 5 PERFORMANCE RANGE AND ENDURACE Range and Endurance values for a T O Weight of 920 kg 2028 Ibs including fuel for warm up and Take Off from SL max continuous Power climb to cruising altitude and a reserve of 21 liters 5 5 US Gal for 45 minutes with 45 Power 2 liters 0 53 US Gal unusable fuel is taken into account At ISA Conditions PA Eng Manif Power Setting Fuel TAS IAS Endur Range Mixture Press Consumption ft RPM IN HG 96 Hp Kts Kts h NM Best 2000 2400 25 1 75 225 68 7 18 2 167 6 160 2 40 401 2200 24 2 65 195 50 5 13 3 159 3 152 3
49. be observed in determining whether the equipment and or system is 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 1 In some airspaces Mode S Elementary Surveillance functionality is required Page Date 31 January 2006 2 13 Section 2 Pilot s Operating Handbook Limitations XTRA EXTRA 3005 Left blank intentionally 2 14 Page Date 20 April 2002 gea XTRA SECTION 3 EMERGENCY PROCEDURES Table of Contents Paragraph Page 3 0 INTRODUCTION EE DR 3 3 3 0 1 ele 3 3 3 0 2 General Behaviour In Emergency Situations 3 3 3 1 AIRSPEEDS FOR EMERGENCY OPERATION 3 4 3 2 OPERATIONAL CHECKLIST ea ooceae r
50. country flight a mor relaxed streched seating position is possible A full travel from the most rearward to the most forward position takes approximately 15sec SECONDARY CONTROL The elevator trim control is located on the right side in the cockpit The actuation is a fail safe design to prevent flutter in case of a single control joint failure 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 The handle is used for locking as well as for normal operation and for emergency release The starter magneto switch is located on the left side of the instrument panel INSTRUMENTATION Standard equipment incorporates a magneto compass an airspeed indicator altimeter fuel gauges engine RPM and manifold pressure fuel flow indicator as well as an ampermeter and a low voltage warning Furher dual instruments exhaust gas cylinderhead temperature indicator and oil temperature pressure indicator are installed 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 Page Date 20 April 2002 7 5 Section 7 Nei Pilot s Operating Handbook Description and Operation of Aircraft and Systems X TRA EXTRA 300S 7 6 1 INSTRUMENT PANEL For instrumet panel arrangement of the cockpit refer to Fig 7 6 1 which includes standard and o
51. 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 R During normal operation the tachometer presents the average of the left and right internal tachometers on the display However a mechanism exists to mask either tachometer from the display leaving the remaining tachometer to determine magneto ignition problems Page Date 20 April 2002 905 5 Section 905 Pilot s Operating Handbook Digital RPM Indicator XTRA EXTRA 300S 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 DIM Quickly pressing and releasing the middle button DIM causes the tachometer to alter nately dim or brighten the LED indicators except the large red LED of the RPM Range 905 8 HANDLING SERVICING AND MAINTENANCE Not affected 905 6 Page Date 20 April 2002 XTRA SECTION 906 LONG RANGE WING TANK CAPACITY Table of Contents Paragraph Page 906 1 GENERAL cco 9
52. 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 31 January 2006 917 3 Section 917 Pilot s Operating Handbook BENDIX KING KT 76A Transponder XTRA EXTRA 3005 917 FUNCTION SELECTOR KNOB The following operating modes can be chosen by the Function Selector Knob OFF Powers off the KT 73 When the unit is turned to another mode it will reply or squitter within two seconds according to the selected mode FLT ID Selects the Flight ID mode displaying the 8 character Flight ID or registration marking of the airplane When in Flight ID mode the transponder will not reply to any interrogations SBY Selects the Standby mode displaying the last active identification code When in Standby mode the transponder is energized but will not reply to any interrogations TST Selects the Test mode displaying all display segments for a minimum of 4 seconds A series of internal tests is performed to check its integrity verify all aircraft specific configuration data and make hardware squitter checks When Flight ID mode the transponder will not repl
53. 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 31 January 2006 913 7 Section 913 Pilot s Operating Handbook FILSER TRT 800 Transponder XTRA EXTRA 300S To meet ICAO specifications the TRT 800 uses an external memory inside the aircraft connector housing of the cable set which is a part of the aircraft Because this cable is installed permanent into the aircraft a change of the transponder will not affect the aircraft address and the Flight ID In the event there is a Cradle error empty memory or data error OUT OF ORDER will be displayed The first line shows which kind of error is present Cradle OFF displayed means no or defective data Cradle displayed means digital checksum error After a few 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 PROCED
54. 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 31 January 2006 Pilot s Operating Handbook TR A EXTRA 300S 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 SCE CON 915 4 Keys for other GTX 330 Functions 915 5 giae AB S T 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 31 January 2006 915 1 Section 915 mE Pilot s Operating Handbook GARMIN GTX 330 Transponder XTRA EXTRA 3005 Left blank intentionally 915 2 Page Date 31 January 2006 Pilot s Operating Handboo
55. 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 903 5 PERFORMANCE Not affected 903 6 WEIGHT AND BALANCE Not affected 903 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 0g milliseconds When properly installed parallel to the line of flight the ELT will not activate due to turbu lence normal operation or aerobatics POINTER PORTABLE ELT MAYOR SYSTEM COMPONENTS The POINTER PORTABLE ELT System consists of the following components Telescopic Whip Antenna Antenna Remote Connector bracket Remote switch ELT mounting optional bracket 903 6 Page Date 20 April 2002 Pilot s Operating Handbook Section 903 EXTRA 300S X TRA Emergency Locator Transmitter OPERATING INSTRUCTION OF THE TRANSMITTER The operation of the ELT is possible over the master unit switch or over the remote switch optional in the panel UNIT MASTER SWITCH ON used to activate the transmitter for test or emergency s
56. 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 analysis are displayed in the second line LIST OF POSSIBLE ERRORS 1 ANT will appear if the antenna is defective e g broken cable 2 FLerr instead of the altitude appears on the display if there is an error with the altimeter or if the aircraft is outside the altitude range FL 010 to FL350 If the mode ACS was active before it will change to mode A S automatically 3 DC for a faulty transmitter power supply 4 FPG for internal communication errors 5 will appear for transmitter error In this case the unit will change to STBY and will stop all transmission Page Date 31 January 2006 912 7 Section 912 Pilot s Operating Handbook FILSER TRT 600 Transponder XTRA EXTRA 3005
57. 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 300S X TRA 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 O 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 Segment lin 90 diving Throttle must be reduced to idle in order to avoid exceeding 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 sh
58. 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 c To level the aircraft the tail wheel is rested on 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 XTR A EA 3005 Section 9 901 902 903 904 905 906 907 908 909 910 911 912 913 914 915 916 917 918 919 920 JE SECTION 9 SUPPLEMENTS Doc No EA 04701 1 Table of Contents Pages Supple mehls 4p Steerable Tail Wheel 4p Electronic Accelerometer ccccccesseeeeceeeeeseneneceeeeessneneeeeeeeseneeeseeeeessneeeeeeeeesesneee 10 p Emergency Locator Transmitter 1 eere nnn 8 p i2udnrbxlgqe e 6 p Digital RPM IndiCatOr
59. re ne ud 1 3 1 2 MANUFACTURER t 1 3 1 3 TECHNICAL TAI 1 3 1 3 1 e A VABIC Io EE 1 3 1 3 2 1 4 1 3 3 EET 1 4 1 3 4 Horizontal m 1 4 1 3 5 1 4 1 3 6 Vertical P 1 4 1 3 7 RU 1 4 1 4 ENGINE o Eccc 1 5 1 5 PROPELLER M 1 5 1 5 1 Exhaust Systems Optional 1 5 1 6 ge E Dd UE 1 5 1 7 OIL P XI 1 5 1 8 Keil ce 1 6 1 9 jiz isec cEc 1 6 1 10 SECONDARY TERMINOLOGY 1 7 Page Date 31 January 2006 1 1 Section 1 Pilot s Operating Handbook General XTRA EXTRA 300S Left blank intentionally 1 2 Page Date 20 April 2002 Pilot s Operating Handbook Z Section 1 EXTRA 3005 XTRA General 1 0 DESCRIPTION This description belongs to aircraft type EXTRA 300 S with nationality and registration marks Manufacturing The airframe is built of tig welded steel tube construction Wings rudder andlanding gearare manufactured of composite material The aircraft is a one seater 1 1 SPECIFICATION OF CLASS The aircraft is certified in normal and acrobatic category LBA Certificate No 1086
60. 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 31 January 2006 Pilot s Operating Handbook E Section 912 EXTRA 3008 XTRA FILSER TRT 600 Transponder The Aircraft Identification FID code is displayed on the right bottom line and consists of seven alphanumerical characters CAUTION The ICAO Flight Plan specifies only 7 characters as Flight Identification Filser reserves 8 characters as stated in ED 73B for further expansion of the flight plan The user shall only program 7 characters for FID SELECTING FLIGHT IDENTIFICATION By pressing the button FID for more than 3 seconds the unit will change into the Flight Identification input menu This FID code is a changeable alphanumerical flight number The right lower knob is used to set the cursor position flashing and with the left lower knob the figures A Z blank and 0 9 can be selected To enter the code press the MODE button
61. with 6 30 0 21 R Hoses in Eng Comp firesleeve 1 Set Fuel Oil amp Sens Parker Stratoflex PTFE Type 124J 4 90 0 21 A Hoses in Eng Comp Aeroquip or AE466 1 Set Fuel Oil amp Sens Parker Stratoflex PTFE Type 124J 3 70 0 15 A Hoses in Eng Comp or Aeroquip or AE466 single Oil Cooler Sys 1 Set Fuel Hoses div MS28741 2 10 0 40 R in Cabin Comp 1 Set Fuel Hoses Parker Stratoflex PTFE Type 124 1 40 0 40 A in Cabin Comp or Aeroquip or 666 1 Sens Hoses Knapp Hoerbiger HS3MA OR H3MM 0 15 0 82 A Cil Fuel amp MA Press 1 RPM Vernier Control ACS Products Co A 750 30 1080 0 65 0 60 R 1 Mixture Vernier Control ACS Products A 750 20 1080 0 65 0 63 R 1 Throttle Control Teleflex Marine F303 03000 0 53 0 40 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 31 January 2006 Pilot s Operating Handbook XTRA Section 6 EXTRA 300S Weight and Balance and Equipment List QTY ITEM MANUFACT PART OR P
62. 0 0 20 Smoke System without Pumps 2 Smoke Oil Pump ITT Jabsco 8860 1203 3 60 0 20 Inject and Refill 2 Smoke Oil Pump ITT Jabsco 23620 3003 4 40 0 20 Inject and Refill 1 Smoke Oil Pump Johnson F3B 19 12V 2 00 0 05 Injection 1 Smoke Oil Pump Johnson F2P10 19 12V 1 65 0 35 Refill 1 Single Pump EXTRA 84112 6 80 0 19 Smoke System incl Pump Marco UP3 OIL12V 1 Airtow Hook EXTRA TOST 83607A0 0 50 5 10 1 2 Sighting Dev LH RH EXTRA 84801 10 each 0 44 1 25 1 Aresti Card Holder EXTRA Assy 0 09 1 32 2 Wing Tie Down Rings EXTRA 83801 2 01 0 04 0 95 Page Date 20 September 2006 6 13 Section 6 Pilot s Operating Handbook Weight and Balance and Equipment List XTRA EXTRA 300S Left blank intentionally 6 14 Page Date 31 January 2006 Pilot s Operating Handbook EXTRA 3005 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 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 THEAIRCGRAETE E T M 7 3 FUSELAGE esis cect M 7 3 WINGS oe 7 4 dice 7 4 FLIGHT CONTROL 5 5 7 5 Primary Control System e 7 5 Longitudinal Flight Control Sy
63. 00 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 31 January 2006 Pilot s Operating Handbook E Section 919 EXTRA 3005 BECKER 4401 Transponder 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
64. 06 3 906 2 LIMITA ONS eee 906 3 906 3 EMERGENCY PROCEDURES lt 906 3 906 4 NORMAL PROCEDURES 906 3 906 5 lddlizeliLulem MN 906 4 906 6 WEIGHT AND BALANCE ntur nin nine nata ru an sena ee eoa 906 5 906 7 DESCRIPTION OF THE SYSTEM 906 5 906 8 HANDLING SERVICING AND MAINTENANCE 4 2 4 44 122111 906 5 Page Date 20 April 2002 906 1 Section 906 Z Pilot s Operating Handbook Long Range Wing Tank Capacity XTRA EXTRA 300S Left blank intentionally 906 2 Page Date 20 April 2002 Pilot s Operating Handbook Section 906 EXTRA 300S XTRA Long Range Wing Tank Capacity 906 906 1 906 2 906 3 906 4 LONG RANGE WING TANK CAPACITY GENERAL The leading edge wing tank on the EA 300 S equipped with the long range tank capacity features two tank compartments on either wing side The compartments are separated by a slosh rib LIMITATIONS FUEL Minimum grade aviation gasoline 100 100LL for alternate fuelgrades see latest revision of Lyc 5 1 No 1070 Total fuel capacity 205L 54 1 US Gallons Wingtanks 154 L 2 x 77 L 40 7 US Gallons Acro amp Center
65. 2 Fuel shutoff valve OFF Pull amp Turn 3 Master switch OFF 4 Airspeed 100 KIAS find your airspeed attitude which will keep the fire away from the cockpit 5 Land as soon as possible 3 5 ICING 3 5 1 INADVERTED ICING ENCOUNTER 1 Turn back or change altitude to obtain an outside temperature that is less conductive to icing 2 Plan a landing at the nearest airfield With extremely rapid ice build up select a suitable off airport landing field 3 6 UNINTENTIONAL SPIN Refer to section 4 Normal Procedures acrobatic maneuver spin recovery 3 7 MANUAL BAIL OUT When in an emergency situation that requires abandoning the aircraft and while wearing a parachute which is at least strongly recommended for acrobatics Reduce speed to 100 Kts if possible Pull mixture to lean Open canopy the low pressure over the canopy in normal flight will flip the canopy fully open immediately Take off headset Open seat belt Leave airplane to the left side Try to avoid wing and tail Open parachute Page Date 31 January 2006 3 7 Section 3 Pilot s Operating Handbook Emergency Procedures X TRA EXTRA 3005 3 8 EMERGENCY EXIT AFTER TURN OVER 1 Master switch OFF 2 Fuel shutoff valve OFF Pull amp Turn 3 Seat belts OPEN 4 Parachute harnesses OPEN 5 Canopy handle PULL TO OPEN WARNING If canopy fails to open break the canopy 6 Aircraft EVACUATE ASAP 3 9 ELEVATOR CONTROL F
66. 2 54 cm m Meter L Litres Gal US gallon 3 79 litres Qts US quart 0 946 litres 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 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 Date 20 April 2002 1 7 Section 1 Pilot s Operating Handbook General XTRA EXTRA 300S Left blank intentionally 1 8 Page Date 20 April 2002 Pilot s Operating Handbook XTR A EXTRA 3005 SECTION 2 LIMITATIONS Table of Contents Paragraph Page 2 1 GENERAL ici 2 3 2 2 AIR SPEED AS ssicscice c 2 3 2 3 CROSS WIND COMPONENT 2 3 2 4 ENGINE e 2 3 2 4 1 Gem nahi nes held 2 4 2 4 2 ec 2 4 2 5 PROPELLER 2 5 2 6 WEIGHT 2 5 2 7 2 22 2
67. 20 April 2002 907 1 thru 907 6 20 April 2002 3 1thru 3 4 20 April 2002 cce citrate 20 September 2006 31 January 2006 908 2 E 20 April 2002 t RE 20 April 2002 908 3 thru 908 8 20 September 2006 31 January 2006 909 thru 911 eret reserved BO Y 20 April 2002 912 1 thru 912 8 31 January 2006 C 31 January 2006 913 1 thru 913 8 31 January 2006 4 2thru 4 7 20 April 2002 914 1thru 914 6 31 January 2006 31 January 2006 915 1thru915 8 31 January 2006 4 9thru 4 12 20 April 2002 916 1 thru 916 6 31 January 2006 5 1 thru 55 14 20 April 2002 917 1thru 917 8 31 January 2006 6 1thru6 2 20 April 2002 918 1 thru 918 6 31 January 2006 31 2006 919 1thru 919 8 31 January 2006 6 4 thru 6 9 20 April 2002 920 1 thru 920 10 31 January 2006 6 10thru 6 11 31 January 2006 Page Date 20 September 2006 EXTAASOOS XTRA SECTION 1 GENERAL Table of Contents Paragraph Page 1 0 DESCRIPTION Pr H 1 3 1 1 SPECIFICATION OF CLASS ute e Ce ge tere v
68. 3 3MM 0 09 1 30 A Oil Temp Ind 2 1 4 or 2DA3 3KV Oil Temp Sender Westach W399 S9 0 08 0 11 A Oil Press Sensor Mediamate 387 100MM 0 12 0 04 A or 387 100KV 1 Stall Sensor EXTRA 73106 1 0 07 0 27 R 1 Stall Warning Horn EMAG EM S 110P 0 13 1 20 R 1 G Meter EXTRA DSA 12 0 37 1 28 1 G Meter Kollsman or Pioneer AN5745 0 40 1 28 O or Bendix 1 G Meter EZE Technologies DA 55 0 16 1 28 1 ELT and Antenna Pointer 3000 10 0 90 0 72 1 Turn amp Bank Ind United Instruments 9501 2 TSO C3b 0 55 1 28 1 Turn amp Bank Ind Castleberry C101 TSO C101T 0 55 1 28 1 Altimeter United Instruments UI5934PD 3 A 134 0 60 1 30 R Page Date 31 January 2006 Section 6 XTRA Pilot s Operating Handbook Weight and Balance and Equipment List EXTRA 3005 QTY ITEM MANUFACT PART OR P N WEIGHT ARM IF REQUIRED R KG m INSTALLED OPTIONAL O ALTERNAT A 1 Altimeter metric Winter 4110 0 33 1 30 A 1 Altitude Encoder ACK A 30 0 15 0 95 1 Airspeed Ind Winter 6533 321 0 21 1 29 R 1 Airsp Ind metric Winter 6531 321 0 21 1 29 A 1 Airspeed Ind United Instruments UI8030 B 835 0 22 1 29 A 1 EGT CHT Westach 2DA1 0 07 1 30 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 28 R Fuel Flow Ind 1 VHF Radio Becker AR 3201 0 90 1 26 R 1 VHF Radio Becker AR 4201 0 67 1 26 A 1 GPS
69. 5 185 Landing Approach 75 80 On Final 65 70 Go Around Speed 90 100 Recommended Airspeed For Flight In Rough Air maximum VA 158 VA 140 Max Demonstrated Cross Wind Component 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 Checklist for daily check and inspections see Section 8 Handling Servicing and Maintenance Page Date 20 April 2002 4 3 Section 4 Normal Procedures XTRA Pilot s Operating Handbook EXTRA 300S 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 42 CHECKLIST PROCEDURES 1 Cockpit NOOR Pilot s Operating Handbook Airplane weight and balance lgnition switch Master switch Fuel quantity indicators Master switch Fuel selector NOTE AVAILABLE CHECKED OFF ON CHECK OFF ACRO amp CENTER TANK Although safe operation did not require the use of the tanks in a specific sequence it is recommended to set fuel selector to ACRO amp CENTER TANK pos
70. 9 9 134 3 59 502 Economy 4000 2400 24 6 75 225 68 7 18 2 170 9 158 1 91 324 Power 2200 23 7 65 195 50 13 3 162 4 150 2 59 418 Economy 2000 23 0 55 165 42 6 11 3 153 1 142 3 06 467 Economy 2000 19 7 45 135 36 5 9 6 142 6 133 3 59 507 Economy 6000 2200 23 2 65 195 50 5 13 3 165 6 149 2 57 422 Economy 2000 22 5 55 165 42 6 11 3 156 1 141 3 04 472 Economy 2000 19 3 45 135 36 5 9 6 145 4 131 3 53 512 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 Economy 2000 18 4 45 135 36 5 9 6 151 4 129 3 48 522 Economy 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 2400 17 0 55 165 46 7 12 3 169 4 135 2 71 446 Economy 2075 17 7 45 135 37 1 9 8 157 8 122 3 36 520 Economy NOTE For temperatures above below Standard ISA increase decrease Range 1 7 and Endurance 1 1 for each 10 C above below Standard Day Temperature for particular 2 Best Power or Best Economy see latest issue of Textron Lycoming Operator 5 altitude Manual 4 10 Series AEIO 540 Page Date 20 April 2002 5 13 Section 5 XTRA Pilot s Operating Handbook Performance EXTRA 300S 5 11 LANDING PERFORMANCE
71. 90 KG from Empty Weight to Point 5 Now follow line Fuel 171 L via point 6 and 7 to point 8 FIND Weight 823 kg 1815 Ibs C G 58 8 cm 23 1 inch 6 3 2 Weight and Balance Record Sheet EMPTY WEIGHT PILOT FUEL ACRO TANK FUEL CENTER TANK FUEL WING TANK xo EOWXX _ 1815 0 1 5 MOMENT E WxX Page Date 20 April 2002 Section 6 2 Pilot s Operating Handbook Weight and Balance and Equipment List XTRA EXTRA 300S 6 4 LOADING WEIGHTS AND MOMENTS WEIGHT PILOT PILOT Pilot REAR SEAT POSITION FRONT SEAT POSITION Parachute ARM 190 cm 75 inch ARM 170 cm 67 inch MOMENT KG x CM INCH x LBS 11400 10200 8855 12350 11050 9593 13300 11900 10331 14250 12750 11068 15200 13600 11806 16150 14450 12544 17100 15300 13282 FUEL IN SYSTEM MAX 171 LITER 45 1 US GAL ACRO amp CENTER TANK WING TANKS LITER KG KG x CM KG KG x CM US GAL LBS IN LBS LBS IN x LBS 10 2 6 20 5 3 40 10 6 60 15 9 80 21 1 100 26 4 120 81 7 6 8 Page Date 20 April 2002 Pilot s Operating Handbook Section 6 EXTRA 3005 XTRA Weight and Balance and Equipment List 6 5 WEIGHTS AND MOMENT LIMITS WEIGHT kg Ibs 950 2028 900 1985 850 1874 820 1808 800 1764 750 1654 700 1544 650 1433 600 1323 EXAMPLE 750 KG 1654 LBS AND 44000 38197 IN LBS CG LOCATION
72. 905 4 Page Date 20 April 2002 Pilot s Operating Handbook Section 905 EXTRA 300S 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 fractional portion 0000 of the current accumulated engine hours When the button is released the fractional part of the engine hours 00 is displayed for a short period of time The clock is started whenever the engine RPM exceeds 800 RPM and is recorded in real hours Clear Clear The middle button clears the RPM trap During depression of the switch the RPM trap is zeroed When the button is released the trap will record the current
73. A 300S 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 EE 913 5 Error Reporting Fault 913 7 LIMITATIONS 2 913 8 EMERGENCY PROCEDURES 913 8 NORMAL PROCEDURES 2 2 913 8 azizelll bie 913 8 Page Date 31 January 2006 913 1 Section 913 mE Pilot s Operating Handbook FILSER TRT 800 Transponder XTRA EXTRA 300S Left blank intentionally 913 2 Page Date 31 January 2006 Pilot s Operating Handbook 7 Section 913 EXTRA 3005 XTRA FILSER TRT 800 Transponder 913 1 GENERAL The TRT 800 is Level 2es Class2 SSR Mode S Elementary and Enhanced Surveillance Transponder It has Mode A Mode A C and Mode S capability In Mode S the transponder provides acquisition and extended squitter capability Furthermore the TRT 800 has a built in barometric pressure altitude coder in 100 ft increments NOTE Refer to latest edition of Filser TRT 800 Pilot s Operation Manual Doc No 03 210 010 11 to get familiar with the TRT
74. AILURE 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 landing trim nose up and establish a shallow descend by adjusting throttle To flair the plane gently increase power to bring the nose up to landing attitude 3 8 Page Date 20 April 2002 EXTRASOOS XTRA SECTION 4 NORMAL PROCEDURES Table of Contents Paragraph Page 4 0 cizizi 4 3 4 0 1 Airspeeds for Normal 4 3 4 0 2 Checklist and Procedures ceteri breed ead era ea 4 3 4 1 PREFLIGHT INSPECTION 22 4 4 4 1 1 Exterior Inspection nens 4 4 4 1 2 S 4 4 4 3 STARTING PROCEDURES 0 4 6 4 3 1 Gold EIA SS stet ou cg ce odes cea dan Seu as cee dua esas cet rere 4 6 4 3 2 FOL EMQG Siz ee E 4 6 4 4 TAXIING THE 4 6 4 5 TAKE OFF PROCEDURE iet duae 4 7 4 5 1 Ke 4 7 4 5 2 IECIT 4 7 4 6 CLIMB e
75. AINTENANCE 2 44 22221 902 9 Page Date 20 April 2002 902 1 Section 902 Z Pilot s Operating Handbook Electronic Accelerometer XTRA EXTRA 300S Left blank intentionally 902 2 Page Date 20 April 2002 Pilot s Operating Handbook Section 902 EXTRA 300S X TRA Electronic Accelerometer 902 ELECTRONIC ACCELEROMETER 902 1 GENERAL The standard equipped accelerometer typ AN 5745 can be replaced by an optional Digital Solid State Accelerometer DSA 12 902 2 LIMITATIONS The instrument markings and placards are provided for the acrobatic category only 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 5 Instrument markings Electronic Accelerometer DSA 12 red range 12g 10g yellow range gt 10g 8g green range gt 8g yellow range 860 410g red range 109 120 902 3 EMERGENCY PROCEDURES Not affected 902 4 NORMAL PROCEDURES Not affected 902 5 PERFORMANCE Not affected 902 6 WEIGHT AND BALANCE Not affected 902 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 o
76. 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 SERVICING E M M 8 3 8 6 GROUND rpillcm 8 4 Page Date 20 April 2002 8 1 Section 8 Pilot s Operating Handbook Handling Servicing and Maintenance XTRA EXTRA 300S Left blank intentionally 8 2 Page Date 20 April 2002 Pilot s Operating Handbook Section 8 EXTRA 300S 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 INSPECTION PERIODS As required by national operating rules all airplanes must pass a complete annual inspection every twelve calendar months In addition to the annual inspection airplanes must pass a complete inspection after every 100 flights hours with a minor check after 50 and 25 hours The Airworthiness A
77. AL 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 31 January 2006 Pilot s Operating Handbook X TRA EXTRA 300S Paragraph SECTION 0 PUBLICATION GUIDANCE Table of Contents Page INTRODUCTION mer 0 3 NOTES 0 3 WARNINGS CAUTIONS AND NOTES es 0 4 LOGOFEEFEFECTIVEIRAGES wa 0 5 Page Date 20 April 2002 0 1 Section 0 Pilot s Operating Handbook Publication Guidance XTRA EXTRA 300S Left blank intentionally 0 2 Page Date 20 April 2002 Pilot s Operating Handbook Section 0 EXTRA 300S XTRA 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 Flugzeugproduktions 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 exchanged and no alterations of or additions to the approved contents may be made without theEXTRA Fl
78. CRAFT 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 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 31 January 2006 920 7 Section 920 Pilot s Operating Handbook BECKER ATC 6401 Transponder XTRA EXTRA 3005 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 fli
79. ENGINE POWER k Seat belt shoulder harness 2 Airspeed 3 Selected field Master switch Touchdown Ignition switch Mixture Fuel shutoff valve Brakes SECURE 80 KIAS FLY OVER noting terrain and obstructions then reaching a safe altitude and airspeed OFF SLIGHTLY TAIL LOW OFF IDLE CUT OFF OFF Pull amp Turn APPLY HEAVILY Page Date 31 January 2006 Section 3 Emergency Procedures XTRA Pilot s Operating Handbook EXTRA 3005 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 WARNING CONTINUE to get a start which would suck the flames and accumulated fuel through the air inlet and into the engine OFF Pull amp Turn 1700 RPM for one minute SHUT DOWN ABANDON aircraft and inspect for damage EXTINGUISH using fire extinguisher if available Do not open engine compartment access doors while engine is on fire 3 4 2 IF ENGINE FAILS TO START 1 Cranking 2 Throttle 3 Mixture 4 Fuel shutoff valve If fire is extinguished 5 Master switch 6 Ignition switch 7 Engine compartment CONTINUE FULL OPEN IDLE CUT OFF OFF Pull amp Turn OFF OFF INSPECT Page Date 20 April 2002 Pilot s Operating Handbook Section 3 EXTRA 300S XTRA Emergency Procedures 3 4 3 ENGINE FIRE IN FLIGHT 1 Mixture IDLE CUT OFF
80. FR1 push button F orthe VFR2 push button G wit hin 3 seconds to store the code under the corresponding button d If neither button is pressed within seconds the flashing stops and the storage operation is aborted NOTE If one of the two buttons F or G is pressed without the STO button having been pressed beforehand then the stored code allocated this button appears in the code display and is switchedto active after 3 seconds can be changed inthe configuration mode If the same button is again pressed within 3 seconds the previous code appears 2 Activation of the VFR codes a Pressthe VFR push button 1 or 2 F G The selected code is then displayed After 3 seconds the displayed code becomes activate and overwrites the previously set reply code b Pressing button F or G again within 3 seconds reactivates the previously set reply code NOTE When the unit is delivered the store buttons are not assigned a code This means that if these buttons are pressed for 0 5 seconds is shown in the code display and the transponder then switches back to the previously active code IMPORTANT CODES 1200 The VFR code for any altitude in the US Refer to ICAO standards elsewhere 7000 The VFR code commonly used in Europe Refer to ICAO standards 0021 The VFR code commonly used in Germany default is set to 0021 at time of installation 7500 Hijack code Aircraft is subject to unlawful interference 76
81. 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 for obtaining the proper license before using the transponder Refer to Becker Pilot s Guide Page Date 31 January 2006 920 3 Section 920 Pilot s Operating Handbook BECKER ATC 6401 Transponder XTRA EXTRA 3005 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 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
82. 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 Smo king is prohibited STRUCTUAL TEMPERATURE COLOUR LIMITATION Structure is qualified up to 72 C 161 6 F Structure temperatures composite above 72 C 161 6 F are not permitted Not to exceed this temperature limit color specification for composite structure manufacturer document EA 03205 19 has to be complied with MAXIMUM OPERATING ALTITUDE Max certified operating altitude is 16000 ft MSL 4877 m TIRE PRESSURE The tire pressure is 2800 hpa 40 2 psi MARKINGS AND PLACARDS AIRCRAFT IDENTITY PLACARD OMANUFACTURER EXTRA FLUGZEUGBAU GMBH FLUGZEUGPRODUKTIONS MODEL EA 300 S UND VERTRIEBS GMBH SERIAL NUMBER MODEL EA 300 S oTC NUMBER o SERIAL NUMBER O TC NUMBER A67EU Page Date 20 September 2006 2 7 Section 2 Pilot s Operating Handbook Limitations XTRA EXTRA 3005 2142 OPERATINGPLACARDS V 158 KTS ACRO near airspeed indicator V 140 KTS NORMAL THE MARKINGS AND PLACARDS INSTALLED IN left side under canopy THIS AIRPLANE CONTAIN OPERATING LIMITATIONS frame WHICH MUST BE COMPLIED WITH WHEN OPERATING THIS AIRPLANE IN THE ACROBATIC CATEGO
83. L 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 selector valve 4 Master switch 5 Airspeed Land If fire persists or aircraft is uncontrollable and wearing a parachute MO SMOKE IN THE COCKPIT 1 Switch SMOKE ARM 2 Bad weather window 3 Ventilation 4 f smoke persists in the cockpit land NORMAL PROCEDURES IDLE CUT OFF OFF Pull amp Turn OFF 100 KIAS find your airspeed attitude that will keep the fire away from the cockpit AS SOON AS POSSIBLE BAIL OUT OFF OPEN OPEN AS SOON AS PRACTICAL 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 2 Switch SMOKE REFILL CONNECT hose nipple to quick connector at the fuselage bottom IMMERSE the other end into the paraffin oil in the canister barrel ON NOTE The refilling should start within max 30 sec If this is not the case the refill lines fittings and filter if installed have to be checked for soiling or leaks Refilling procedure can be supported by reducing the suction height e g lifting the canister The fully filled status is sensed by the floating device which automati
84. 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 920 kg 2028 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 171L 45 17 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 143L 37 8 US Gal Range 415 NM 768 km Endurance 2 49 HRS 5 4 Page Date 20 April 2002 Pilot s Operating Handbook Z Section 5 EXTRA 300S Performance 5 2 ISA CONVERSION ISA Conversion of pressure altitude and outside air temperatur TEMPERRTURE F 80 40 40 80 120 16 15 14 a 12 ger 11 Be po 9 2 7 5 5 5 v 4 3 2 1 60 40 20 20 40 360 TEMPERATURE Page Date 20 April 2002 5 5 Section 5 2 Pilot s Operating Handbook Performance EXTRA 3005 5 3 kts 27 IBS INDIGBHTED AIRSPEED 220 210 200 AIRSPEED CALIBRATION 190 180 170 160 150 140 130 120 110 100 90 80 70 60
85. 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 on the right side the ident window FLT IDT The FLT IDT is annunciated and the flight ID is illuminated in the display area when the FLT ID mode is selected by the Function Selector Knob TEST TEST is displayed in the Test mode if no faults are detected SBY FXYZ If one or more fault is detected the Test mode SBY is displayed in the altitude window and the ident window will cycle through all detected faults indicated by FXYZ The XYZ denotes the specific fault 917 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
86. Moment kg cm Wt kg Moment kg cm lbs inch lbs inch lbs lbs inch Empty weight as delivered Page Date 20 April 2002 Pilot s Operating Handbook Z Section 6 EXTRA 3005 XTRA Weight and Balance and Equipment List 6 3 CENTER OF GRAVITY CALCULATION SAMPLE PROBLEM FUEL IN FUEL IN FUEL IN ACRO TANK CENTER TANK WING TANK Position 9 LTR 42 LTR 120 LTR 2 37 US GAL 11 1 US GAL 31 7 US GAL kg 105 kg Ibs OO Page Date 20 April 2002 6 5 EXTRA 300S Pilot s Operating Handbook XTRA Weight and Balance and Equipment List Section 6 S3HONII 972 9 9 ec 442 261 221 WO WHY 0 0 099 0 09 089 0 08 osr CENTER OF GRAVITY CALCULATION SAMPLE PROBLEM 009 0 00L lt AldW3 1 22 AINO SJILV8OH V 2 JION 759 gt 09 n amp 941 m 008 1V3 JILVEOUSY MOLW i 7 81 058 006 gag eee a 026 MOLW sql Dy IHSI3M TRO 6 3 Page Date 20 April 2002 Pilot s Operating Handbook EXTRA 300S XTRA Section 6 Weight and Balance and Equipment List 6 3 1 Sample Take off Condition Pilot 90 0 kg Fuel in Acro Tank 91 6 5 kg Fuel in Center Tank 42 L 30 2 kg Fuel In Wing Tank 120 L 86 4 kg Aircraft Empty Weight 610 0 kg 823 1 kg To find C G follow line Pilot
87. 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 32 F 15 C 59 F 30 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 f m ft m ft Ibs 920 80 SL 171 561 527 1729 177 581 548 1798 185 607 586 1923 2028 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 78 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 75 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 3005 Para
88. RY OTHER LIMITATIONS WHICH MUST BE COMPLIED WITH WHEN OPERATING THIS AIRPLANE IN THIS CATEGORY OR IN THE NORMAL CATEGORY ARE CONTAINED IN THE AIRPLANE FLIGHT MANUAL APPLICABLE RPM LIMITATION MUST BE OBSERVED THIS AIRPLANE IS CERTIFICATED on the instrument panel FOR VFR DAY OPERATION OPERATION UNDER KNOWN ICING CONDITIONS PROHIBITED FUEL near each filler cap AVGAS 100 100 LL WING TANK 120L seperate hatch USABLE upper cowling Cue FUEL ACRO amp CENTER gt 49 L USABLE e SELECTOR 12 9 US GAL on right aux spar hardpoint Ud 0 near trim lever at the right side TRIM in the cockpit WING TANK the insrument panel under MUST BE EMPTY FOR ACROBATICS fuel capacity indicator ACRO amp CENTER TANK SHOWS ZERO IN LEVEL FLIGHT BELOW 11 6 L 3 US GAL UNUSABLE FUEL 2 L 0 5 US GAL 2 8 Page Date 31 January 2006 Pilot s Operating Handbook Section 2 EXTRA 300S XTRA Limitations THE REMAINING FUEL IN LEVEL FLIGHT A on the instrument panel CANNOT BE USED SAFELY under the acro amp center tank WHEN INDICATOR READS ZERO fuel capacity indicator ACROBATIC 10G in cockpit MTOW 820 KG 1808LBS NORMAL 6G 3G MTOW 920 kg 2028 LBS ACROBATICS INCL SPIN NOT APPROVED under pump switch on the instrument panel BOOST PUMP on canopy frame
89. Rotate the aircraft at 65 KIAS On reaching climb speed of 100 KIAS reduce the RPM Manifold Pressure to 2400 24 and proceed climbing 4 6 CLIMB Due to noise protection 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 the 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 consumption 4 Trim As required 5 Fuel Check periodically Page Date 20 April 2002 4 7 Section 4 Pilot s Operating Handbook Normal Procedures EXTRA 3005 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 5 Fuel selector amp CENTER TANK NOTE Although safe operation did not require the use of the tanks in a specific sequence it is recommended to set fuel selector to ACRO amp CENTER TANK position 4 8 2 APPROACH 1 Boost pump ON 2 Mixture set to Rich 3 Airspeed reduce to approach speed 4 Propeller pitch set to low angle High RPM NOTE It is recommended to set the RPM to 2400 during approach and lan
90. TRA 3005 Left blank intentionally 916 6 Page Date 31 January 2006 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 deos 917 4 917 1b Gode Selecti M 917 4 917 1c Buttons selectors for other KT 73 917 5 917 1d PUNGCUOIDISDIAY C EE 917 6 917 1e Programming DG 917 6 917 1f 917 6 917 1g Failure etu rese d vie thee Dev respec d de Ead du DS Cm 917 7 917 2 LIMITATIONS 917 7 917 3 EMERGENCY PROCEDUBRES e 917 7 917 4 NORMAL PROCEDURES 917 7 917 5 PERFORMANCE 917 7 Page Date 31 January 2006 917 1 Section 917 mE Pilot s Operating Handbook BENDIX KING KT 76A Transponder XTRA EXTRA 3005 Left blank intentionally 917 2 Page Date 31 January 2006 Pilot s Operating Handbook E Section 917 EXTRA 300S 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 accordin
91. The plane is designed for unlimited acrobatics wing tanks must be empty Inverted flight maneuvers are limited to max 4 min Recommended basic maneuver entry speeds are listed in the following list Recommended entry Maneuvers speeds Symbol Remarks min KIAS max KIAS Segment Horizontal Line e j 45 climbing 80 LM 90 up 158 1 45 diving V Voa Sy reduce throttle 90 diving V Vie 1 reduce throttle 1 4 Loop climb 100 190 2 Looping 100 190 O Stall turn 100 190 Aileron roll 80 158 gt full deflection Snap roll 80 140 7 Tail slide 100 190 E Spin Inverted spin m Knife edge gt 150 Sim 10s Inverted Flight gt V 190 e 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 which exceed the structural capability of the aircraft NOTE For Acrobatic Maneuvers see Section 4 All maneuvers can be performed in positive and negative flight attitude 2 6 Page Date 31 January 2006 Pilot s Operating Handbook Section 2 EXTRA 300S lt XTRA Limitations 2 9 2 9 1 2 9 2 2 10 2 11 2 12 2 13 2 14 2 14 1 LOAD FACTOR NORMAL FLIGHT 6 g 3 g for MTOW 920 kg 2028 Ibs ACROBATIC FLIGHT 10g 10g for MTOW 820 kg 1808 Ibs
92. URES 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 31 January 2006 Pilot s Operating Handbook TR A EXTRA 300S 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 tenete Ene Ee RR 914 4 LIMITATIONS 222 914 5 EMERGENCY PROCEDURES 914 6 mMponant CodeS E 914 6 NORMAL PROCEDURES 914 6 PERFORMANCE 914 6 Page Date 31 January 2006 914 1 Section 914 Pilot s Operating Handbook GARMIN GTX 327Transponder XTRA EXTRA 3005 Left blank intentionally 914 2 Page Date 31 January 2006 Pilot s Operating Handbook Posuit Section 914 EXTRA 3005 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 tr
93. XTRA 3005 5 9 FUEL CONSUMPTION LITER STANDARD DAY HOUR 23 8 90 21 1 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 ONM FUEL CONSUMPTION LITER gt 52 LTR HRS 13 7 GAL HRS gt 3 25 NM LTR 12 3 NM GAL 457 15 1 4 0 557 13 2 3 5 657 11 4 3 0 9 5 2 5 oe 1 0 POWER SL 2000 4000 6000 8000 10000 12000 14000 16000 ft PRESSURE RLT PR 5 12 Page Date 20 April 2002 Pilot s Operating Handbook Section 5 EXTRA 300S XTRA Performance 5 10 CRUISE PERFORMANCE Range and Endurance values for a T O Weight of 920 kg 2028 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 RPM INHG 96 Hp l h Kts Kts NM Best 2000 2400 25 1 75 225 68 7 18 2 167 6 160 1 91 320 Power 2200 24 2 65 195 50 13 3 159 3 152 2 60 413 Economy 2000 23 5 55 165 426 11 3 150 2 144 3 08 462 Economy 2000 20 2 45 135 36 5 9 6 13
94. able 907 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 907 7 Section 907 Z Pilot s Operating Handbook Airtow Hook EXTRA 3008 blank intentionally 907 8 Page Date 20 April 2002 pues XTRA SECTION 908 SMOKE SYSTEM Table of Contents Paragraph Page 908 1 ssc 908 3 908 2 LIMITAT ON S 908 3 908 3 EMERGENCY PROCEDURES 908 4 908 4 NORMAL PROCEDURES 908 4 908 5 PERFORMANCE 908 5 908 6 WEIGHTAND BALANCE 908 5 908 7 DESCRIPTION OF THE SYSTEM 908 6 908 8 HANDLING SERVICING AND MAINTENANCE eese nnne 908 7 XTRA EXTRA 5005 Left blank intentionally laa XTRA 2 908 SMOKE SYSTEM 908 1 GENERAL For performing at airshows the EXTRA 300 S may optionally be equipped with a smoke system 908 2 LIMITATIONS For safe operation of the smoke system the following limitations have to
95. ag 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 the OFF position ACS is the default operation mode and the transponder replies to Mode A C and S interrogations The pressure altitude will be displayed as Flight Level SQUAWK SELECTION Squawk selection is done with the four rotating knobs to provide 4096 identification codes The assignments of the knobs starting at top left are X selection of thousands 0 7 X selection of hundreds 0 7 X selection of ten 0 7 X selection of one 0 7 The code is entered in the lower line and remains inactive By pushing the UP AND DOWN ARROWS button the squawk code is transferred to the upper line and becomes active The code in the upper line is always the active one IMPORTANT CODES 1200 The VFR code for any altitude in the US Refer to ICAO standards elsewhere 7000 The VFR code
96. agraph Page 904 1 904 3 904 2 LIMITATIONS 904 3 904 3 EMERGENCY PROCEDURES secca aie d aano 220 904 3 904 4 NORMAL PROCEDURES 42 entend naeh no ER 904 3 904 5 904 4 904 6 BALANCE 10 11 snnt nsa 904 4 904 7 DESCRITPION OF THE SYSTEM cssccicsevessseesiacesncccenttsqntvstencsconsssepecsttsnnnvcccnattcertestecedsce 904 4 904 8 HANDLING SERVICING AND MAINTENANCE 4 422221 904 5 Page Date 20 April 2002 904 1 Section 904 junii Pilot s Operating Handbook External Power XTRA EXTRA 3005 Left blank intentionally 904 2 Page Date 20 April 2002 Pilot s Operating Handbook Z Section 904 EXTRA 300S XTRA External Power 904 EXTERNAL POWER 904 1 GENERAL The EXTRA 3008 can be equipped with two versions of an optional external power receptacle system The normal system PN 93102 16 01 provides the capability to start the engine independent of the board battery and is limited to this use The continuous operation system PN 93102 16 02 further allows feeding the electrical system for longer periods 904 2 LIMITATIONS T
97. andbook Section 2 EXTRA 300S X TRA Limitations 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 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 210 245 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 G METER green arc 5g 89 yellow arc 89 109 red line 10g FUEL FLOW INDICATOR green arc Ogal h 35gal h red radial 35 gal h Page Date 20 April 2002 2 11 Section 2 Pilot s Operating Handbook Limitations XTRA EXTRA 3005 MANIFOLD PRESSURE INDICATOR green arc 10 Hg 25 Hg yellow arc 25 Hg 29 5 Hg red radial 29 5 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 known 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
98. andling quality the EXTRA 300 S 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 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 ful
99. anopy is manufactured in one section The canopy can be manually operated and opened by lifting to the right Interior canopy locking handles located on the left side on the canopy 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 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 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 Electrosystem Starter B amp C Fuel pump Gates Lear Shielded ignition system Propeller governor drive Transistor voltage regulator The engine is operated with the following manual controls Throttle control RPM control Fuel mixture control The propeller governor monitors the RPM automatically and prevents overspeeding In the event that oil pressure is lost the
100. ansmitting 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 should be turned off before starting or shutting down aircraft engine The GTX 327 Transponder is powered on by pressing the STBY ALT or ON keys or by the AVIONIC MASTER switch After power ona start up page will be displayed while the unit performs a self test 914 1 1 MODE SELECTION KEYS OFF Powers off the GTX 327 STBY Powers on the transponder in standby mode At power on the last active identification code will be selected When in standby mode the transponder will not reply to any interrogations ON Powers on the transponder in Mode A At power on the last active identification code will be selected Inthis mode the transponder replies to interrogations as indicated by the Reply Symbol Replies do not include altitude information ALT Powers on the transponder i
101. anual AIM for a detailed explanation of identification codes Page Date 31 January 2006 918 5 Section 918 mE Pilot s Operating Handbook BECKER ATC 2000 Transponder XTRA EXTRA 3005 918 4 NORMAL PROCEDURES Not applicable 918 5 PERFORMANCE Not applicable 918 6 Page Date 31 January 2006 Pilot s Operating Handbook TR A EXTRA 300S Paragraph 919 1 919 1 1 919 1 2 919 1 3 919 1 4 919 1 5 919 1 6 919 1 7 919 1 8 919 2 919 3 919 3 1 919 4 919 5 SECTION 919 BECKER ATC 4401 TRANSPONDER Table of Contents Page GENERAD 919 3 Controls and 919 4 Switching on the unit pre flight 919 4 SOUAWK T eno 919 5 Flight operation in Mode A transponder reply code only 919 7 Flight operation in Mode A C reply code and altitude code 919 7 Squawk Jorit 919 7 es 919 7 Gonfiguration 919 8 ce 919 8 5 919 8 MONTANE CodeS ru c 919 8 NORMAL PROCEDURES 919 8 xen lem PG 919 8 Page Date 31 January 2006 919 1 Section 919 mE Pilot s Operating Ha
102. at 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 a C as first character of the two LC Display lines The Absolute Extreme Values only change if an Instantaneous Value occurs that is greater than the positive Absolute Extreme Value or lower than the negative Absolute Extreme Value TIME AND DATE You can recall the current time and date by pushing the buttons If you want to change the current time and date of the clock you have to enter the security code by the buttons In Case the code is wrong or you wait too long the instrument will return into the Normal Operating Mode The clock module has its own battery power supply backup preventing the clock from stopping even in case of turning off the master switch or disconnecting the DSA 12 from the electrical system of the aircraft Page Date 20 April 2002 902 5 Section 902 Pilot s Operating Handbook Electronic Accelerometer XTRA EXTRA 300S 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 sho
103. be considered 1 Max takeoff weight MTOW 820 kg 2 Specification of the smoke oil Straight paraffin oil viscosity 30 50cts at 20 C 68 F initial boiling point gt 330 C 626 F For example Fauth 05 Texaco Canopus 13 or equivalent 3 Local airfield and weather conditions have to be considered For the prevention of a fire alarm inform the flight control before you activate the smoke system 4 Recommended Manifold pressure min 20 Hg 5 The activation of the smoke system on ground is only allowable for a brief system test 6 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 7 Wearing a parachute is strongly recommended Operating Markings amp Placards SMOKE OIL External Next to the 516919 414929 SWILETT Gi connector the fuse he throttle 40cts 35L 9 2 USC conn he fu rott __ For DUAL PUMP SYSTEM On instrument pa n control switch SMOKE row and circuit breaker r CONTROL OFF SMOKE REFILL __ For SINGLE PUMP SYSTEM On instrument panel E sen control switch SMOKE SYSTEM n in suurment E BREAKER below circuit breaker row row and circuit breaker row XTRA s Operating Handbook EXTRA 5008 EMERGENCY PROCEDURES FAILURE OF THE SMOKE SYSTEM 1 Switch SMOKE ARM and SMOKE REFILL OFF 2 Circuit breaker PUL
104. cally switches the refilling off Page Date 20 September 2001 After automatic refill shut off 3 Switch SMOKE REFILL OFF 4 Refill hose DISCONNECT 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 Hg 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 908 5 PERFORMANCE Not affected 908 6 WEIGHT AND BALANCE e 5 3 294 255 320 384 Specific Weight of the paraffin oil 2 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 Seton 908 XTRA Piot s Operating Handbook 908 7 DESCRIPTION OF THE SYSTEM On pilot s deman
105. 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 31 January 2006 920 5 Section 920 Pilot s Operating Handbook BECKER ATC 6401 Transponder XTRA EXTRA 3005 7777 Military interceptor operations Never squawk this code 0000 Military use Not enterable Avoid selecting code 7500 and all codes in the 7600 7777 range These trigger special indicators in automated facilities Only the code 7500 will be decoded as the hijack code An aircraft s transponder code if available is utilized to enhance the tracking capabilities of the ATC facility therefore care should be taken when making routine code changes Note Unintentional transmission of an emergency code is prevented in that the transponder replies are inhibited whilst the code is being set This applies particularly where the new code is being set in the ON or ALT modes Also if a special code is called up no transponder reply takes place during the period in which the previous code can be reactivated approximately 3 seconds 920 1 5 SQUAWK IDENT After a squawk ident request from ATC press Ident button IDT D briefly This transmits an additional special pulse SPI for approx 18 seconds which enables the aircraft to be clearly identified on the radar screen of the controller Idt appears in the bottom
106. 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 31 January 2006 913 5 Section 913 Pilot s Operating Handbook FILSER TRT 800 Transponder XTRA EXTRA 300S 7700 Emergency 7777 Military interceptor operations Never squawk this code 0000 Military use Not enterable Care should be taken not to select the code 7500 and all codes in the 7600 7777 range which trigger special indicators in automated facilities Only the code 7500 will be decoded as the hijack code An aircraft s transponder code if available is utilized to enhance the tracking capabilities of the ATC facility therefore care should be taken when making routine code changes STANDBY MODE The standby mode is activated by pressing the MODE button once This sets STBY in the mode indicator field The transponder will now only reply to direct addressed Mode S interogations The squitter stays active at a lower rate ALTITUDE OFF Switching off altitude reporting will be necessary if the ATC controller requests it For switching off altitude reporting the MODE button has to be pressed until A S is displayed The altitude display shows FL to indicate that the altitude reporting is not active Now the transponder will reply on Mode C interrogati
107. ctive with Mode C frames only and Mode S with altitude reporting all ZERO only ACS Mode and 5 full active ARROWS UP AND DOWN To activate the inserted SQUAWK CODE fromthe lower standby line to the upper active position the button with the UP AND DOWN ARROWS shall be pressed IDENT The IDENT push button causes the special position identification pulse SPI to be transmitted for a period of 18 seconds FID In the Standby Mode the Aircraft Identification Flight Identification and Aircraft Address can be checked by pressing the push button FID The Flight Identification is displayed on the right side of the lower line By pressing the button FID for more than 3 seconds the input mode can be set or the Flight Identification can be changed FLAGS SQUITTER FLAG When the extended squitter is active the letter S is displayed on the left top side of the display As the squitter is a periodic signal the displayed S is blinking REPLY FLAG In case of the transponder replying to interrogations the letter R is displayed on the left top side of the display 913 4 Page Date 31 January 2006 Pilot s Operating Handbook Z Section 913 EXTRA 300S XTRA FILSER TRT 800 Transponder IN FLIGHT FLAG When there is an undercarriage switch installed the display can toggle between the letters F whether the aircraft is in flight condition or the letter whether the aircraft is in on ground condition The fl
108. d 5 The next digit can be changed with 6 and the same for next digits 7 Fifth push to button C now again first digit is inverted 8 Changes can be stored with STO button at any time inversion stops in this case 9 A VFR code that was preset in this way can be activated as described in chapter VFR Code Activation 10 Atimeout for inversion 10 sec is introduced if no action happens Nothing stored as long as F is not pressed NOTE It is possible to leave the setting procedure with SEL button G at any time and normal mode is available then Indication SEL on the display changes backto mode indication If STO button F was not used no change has been stored 920 1 8 FLIGHT OPERATION IN MODE A C S REPLY CODE AND ALTITUDE CODE 1 When ATC requests the transmission squawk switch the transponder to ALT using mode switch A NOTE In exceptions the altitude has to be turned off i e switch the transponder to ON using mode switch A 2 The transponder replies using the selected Code and in response to mode C interrogation it transmits the altitude of the aircraft to 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 31 January 2006
109. d 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 31 January 2006 Pilot s Operating Handbook E Section 919 XTRA BECKER ATC 4401 Transponder EXTRA 300S 3 After the switch on test has elapsed and no error message is written in the display the transponder switches to the mode set on the mode switch A Note The blind encoder is only powered if the transponder is not switched OFF at least SBY A blind encoder needs a warm up time sometimes a several minutes Therefore although the solid state transponder needs no warm up time turn the transponder to SBY immediately after starting the engine 919 1 3 SQUAWK SELECTION 1 The transponder remains switched in the standby mode until requested by the ground station ATC to transmit a code e g squawk alpha 6426 Using the double rotary switch B C set the 4 digit code requested by ATC as follows Using switch B move the cursor to the particular digit Digits 0 to 7 can then be set using switch C NOTES If switch B is turned clockwise or counter clockwise the cursor is moved one position to the right or the left The cursor appears only in th
110. d the smoke system produces a trail of smoke by injection of smoke oil straight paraffin oil into the engine exhaust The smoke oil is vaporised by the exhaust gas heat and is visible as dense smoke after leaving the exhaust For smoke system activation the SMOKE ARM switch located at the pilot instrument panel needs to be switched ON first The smoke 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 are in the ON position the smoke system is not energized and will not run There are two different systems approved A DUAL PUMP SYSTEM The 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 njection pump in the engine compartment with a shut off solenoid in the pilot compartment ON OFF switch on
111. de entry Returns cursor to last code digit within five seconds after entry Selects changeable fields in Configuration Mode CLR Resets the Count Up and Count Down timers Cancels the previous keypress during code selection and Count Down entry Returns cursor to last code digit within five seconds after entry Used in Configuration Mode 8 Reduces Contrast and Display Brightness when the respective pages are displayed and enters the number eight into the Count Down timer Used in Configuration Mode 9 Increases Contrast and Display Brightness when the respective pages are displayed Also enters the number nine into the Count Down timer Used in Configuration Mode 915 1 4 FUNCTION DISPLAY PRESSURE ALT Displays the altitude data supplied to GTX 330 in feet hundreds of feet i e flight level or meters depending on configuration An arrow to the right of the altitude indicates that the airplane is climbing or descending Page Date 31 January 2006 915 5 Section 915 Pilot s Operating Handbook GARMIN GTX 330 Transponder XTRA EXTRA 3005 FLIGHT TIME Displaysthe Flight Time controlled bythe 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 COUNT UP TIMER The count up tim
112. ding 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 at 80 KIAS 2 Airspeed on final maintain 70 KIAS 3 Elevator trim adjust NOTE Stall speed will be MTOW 820 kg 55 KIAS MTOW 920 kg 59 KIAS 4 8 4 NORMAL LANDING 1 Landing perform as practicable with respect to surface and weather condition 2 Touchdown 8 point landing 4 8 Page Date 31 January 2006 Pilot s Operating Handbook Z Section 4 EXTRA 300S X TRA 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 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
113. e 31 January 2006 Pilot s Operating Handbook 2 Section 920 EXTRA 300S XTRA BECKER ATC 6401 Transponder During the PBIT the is inthe 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 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 Maximum 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 AIR
114. e 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 longer be seen in the display field or the identification Switch is pressed in the ON or ALT mode the code currently set is switched active NOTES Whilst settings are taking place the transmission branch of the transponder is inhibited to prevent unintentional transmission If only two digits were named by ATC 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 31 January 2006 919 5 Section 919 Pilot s Operating Handbook BECKER ATC 4401 Transponder XTRA EXTRA 3005 b Press store push button STO J the set code then flashes c Pressthe V
115. ed landing PERFORM AS PRACTICABLE 3 2 3 ENGINE FAILURE DURING FLIGHT RESTART PROCESS 1 Airspeed 80 KIAS 2 Fuel shutoff valve CENTER TANK 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 EXTRA 3005 XTRA Section 3 Emergency Procedures 3 2 4 3 2 5 3 3 3 3 1 3 3 2 OIL SYSTEM MALFUNCTION If oil pressure indicates low If oil pressure is not regained than 1 Airspeed 2 Throttle 3 Engine oil temperature 4 Land WARNING Apply positive g 80 KIAS REDUCE TO IDLE OBSERVE INDICATION ASAP 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 2 Low voltage monitor 3 Red light off If red light illuminates again 4 Land FORCED LANDINGS SWITCH OFF AND ON CHECK INDICATION CONTINUE FLIGHT AS SOON AS PRACTICAL EMERGENCY LANDING WITHOUT ENGINE POWER Seat belts shoulder harnesses Airspeed Mixture Fuel shutoff valve Ignition switch Master switch Touchdown Brakes SECURE 80 KIAS IDLE CUT OFF OFF Pull amp Turn OFF OFF SLIGHTLY TAIL LOW OPTIMUM BRAKING PRECAUTIONARY LANDING WITH
116. ed to have a lifetime of 5 to 10 years A weak battery can be exchanged by the manufacturer only Page Date 20 April 2002 902 9 Section 902 Z Pilot s Operating Handbook Electronic Accelerometer XTRA EXTRA 300S Left blank intentionally 902 10 Page Date 20 April 2002 Pilot s Operating Handbook XTR A EXTRA 3005 Paragraph 903 1 903 2 903 3 903 4 903 5 903 6 903 7 903 8 SECTION 903 EMERGENCY LOCATOR TRANSMITTER Table of Contents Page cj l 903 3 LIMITATIONS sme 903 3 EMERGENCY 5 e Inr 903 4 NORMAL PROCEDURES aam anat n adde 903 6 PERFORMANCE 903 6 WEIGHT AND BALANCE 903 6 DESCRIPTION AND OPERATION OF THE SYSTEM 903 6 HANDLING SERVICING AND MAINTENANCE 422 221 903 7 Page Date 20 April 2002 903 1 Section 903 Z Pilot s Operating Handbook Emergency Locator Transmitter X TRA EXTRA 3005 Left blank intentionally 903 2 Page Date 20 April 2002
117. eight for the elevator is mounted on the elongated center bracket of the elevator extending into the fuselage 7 4 Page Date 20 April 2002 Pilot s Operating Handbook Section 7 EXTRA 300S X TRA Description and Operation of Aircraft and Systems 7 5 7 5 1 7 5 2 7 5 3 7 5 4 7 5 5 7 6 FLIGHT CONTROL SYSTEM PRIMARY CONTROL SYSTEM The EXTRA 300 5 is standard equipped with conventional stick type control columns and electric adjustable rudder pedals The primary control surfaces are operated through a direct mechanical linkage LONGITUDINAL FLIGHT CONTROL SYSTEM The stick bearing is housed in a torque tube which is also linked to the lateral flight controls The stick movements are transferred to the elevator by a push pull rods LATERAL FLIGHT CONTROL SYSTEM Push 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 DIRECTIONAL FLIGHT CONTROL SYSTEM The rudder pedals with brake pedals are adjustable and operate the rudder through a cable system Springs keep the cables under tension when the pedals are not operated The pedal adjustment is archieved with electric linear actuators The pedal adjustment system provides an in flight capability to adjust the pedals according the the pilot size and operation e i for long cross
118. elts shoulder harnesses ADJUST AND LOCK 4 Canopy CLOSE AND LOCK CAUTION Handles of the canopy lock mechanism must be in the most opposite position indicated with a red line on the canopy frame Check gap between canopy frame and fuselage fairing 5 6 7 8 9 1 Brake Master switch Avionics power switch Electrical equipment Alternator 0 Wingtip position Strobe lights CHECK ON OFF OFF ON ON Page Date 20 April 2002 Section 4 Normal Procedures XTRA nir 4 3 STARTING PROCEDURES 4 3 1 COLD ENGINES The following starting procedures are recommended however the starting conditions may necessitate some variation from these procedures 1 2 Perform pre flight inspection Set propeller governor control in High RPM position Open throttle approximately 1 4 travel Turn boost pump ON 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 Engage starter When engine fires release the ignition switch back to BOTH Move mixture control slowly and smoothly to FULL RICH 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
119. epoxy coating The connection to the fuselage is arranged by two bolts piercing through the spar parallel to the centerline of the fuselage and two brackets at the rear spars Integral fuel cells are provided in the leading edge of the wing extending from the root ribs to half the span of each R L and L H wing The ailerons are supported at three points in spherical bearings pressed into aluminium brackets To reduce pilot s hand forces the hinge line of the ailerons is positioned 25 of the aileron depth at the root and 21 5 at the tip Furthermore the ailerons are equipped with spades to decrease pilot forces Ailerons are controlled via the center bracket To prevent flutter the ailerons are weight balanced in the overhanging leading edge 7 4 EMPENNAGE The EXTRA 300 S 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 elevator due to aerolastic reasons entirely 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 w
120. er 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 MASTER switch is on by pressing the STBY ALT or ON keys After power on a start up page will be displayed while the unit performs a self test Page Date 31 January 2006 915 3 Section 915 Pilot s Operating Handbook GARMIN GTX 330 Transponder XTRA EXTRA 3005 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 onthe transponder in Mode A and Mode C At power on the last active identification code will be selected In ALT mode the
121. er is controlled by the START STOP and CLR keys Pressing the CLR key zeros the display COUNT DOWN The count down timer is controlled by START STOP CLR and CRSR keys The initial Count Down timeis entered with the 0 9 keys Pressing the CLR key resets thetimer to the initial value STBY The transponder will not reply to any interrogations GND This page is not active CONTRAST This page is only displayed if manual contrast mode is selected in Configuration Mode Contrast is controlled by the 8 and 9 keys DISPLAY This page is only displayed if manual backlighting mode is selected on Configuration Mode Backlighting is controlled by the 8 and 9 keys 915 1 5 CONFIGURATION MODE The configuration is normally set at time of installation including the unique Mode S aircraft address The configuration Mode should not be used during flight Refer to the GTX 330 Pilot s Guide PN 190 00207 00 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 31 January 2006 Pilot
122. eral 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 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
123. ered 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 will be saved CRSR Whenin FLT ID mode rotating the CRSR knob 2 1st ATCRBS Code Selector Knob will position the cursor under the character of the flight ID to be changed Page Date 31 January 2006 917 5 Section 917 Pilot s Operating Handbook BENDIX KING KT 76A Transponder XTRA EXTRA 3005 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
124. et clip to release transmitter remove ELT Remove the telescope antenna from the stowage clips and insert into the ANT receptacle 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 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 903 5 Section 903 Pilot s Operating Handbook Emergency Locator Transmitter n X TRA EXTRA 300S 903 4 NORMAL PROCEDURES There is no change of basic normal procedures with the installation
125. f 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 902 8 Page Date 20 April 2002 Pilot s Operating Handbook Section 902 EXTRA 300S 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 902 8 HANDLING SERVICING AND MAINTENANCE If the absolute extreme value C indicates that the operating limits have been exceeded the manufacturer must be informed The battery inside which is used for the clock power supply backup is expect
126. fe 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 S 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 these Supplements and is responsible for edition of revisions The log of effective pages is found under section 0 4 of this Pilot s Operating Handbook Each Supplement section e g steerable tailwheel covers only a single system device or piece of 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 S check mark in the Section column indicates that the corresponding supplement must be included in this POH Page Date 31 January 2006 9 3 Section 9 Pilot s Operating Handbook Supplements XTRA EA
127. fter 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 31 January 2006 916 3 Section 916 Pilot s Operating Handbook BENDIX KING KT 76A Transponder XTRA EXTRA 3005 7600 Loss of communications 7700 Emergency 7777 Military interceptor operations Never squawk this code 0000 Military use Not enterable Avoid selecting code 7500 and all codes in the 7600 7777 range These trigger special indicators in automated facilities Only the code 7500 will be decoded as the hijack code An aircraft s transponder code if available is utilized to enhance the tracking capabilities of the ATC facility therefore care should be taken when making routine code changes 916 1 2 REPLY LIGHT During normal operation the flashing Reply Light indicates thatthe KT 76A is functioning properly and replying to interrogations from ground radar Interrogations occur at 10 15 second intervals corresponding to each radar sweep Frequently the reply light will blink almost continuously meaning that the t
128. g Handbook Airtow Hook XTRA EXTRA 300S Left blank intentionally 907 2 Page Date 20 April 2002 Pilot s Operating Handbook Section 907 EXTRA 300S XTRA Airtow Hook 907 AIRTOW HOOK 907 1 GENERAL The EXTRA 300 5 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 C190 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 m and 60 Ultimate load of the air tow max 850 kp 1875 Ibs If tows with higher ultimate load are used a breaking piece weak links of max 850 kp 1875 lbs needs to be interconnected 907 2 LIMITATIONS For a safe air towing the following points must be observed 1 MTWO of the aircraft 820 kg 1808 Ibs 2 Max empty weight of the aircraft 697 kg 1536 Ibs 3 passenger pilot only CAUTION 4 Min air towing speed 66 KIAS 5 Best air towing speed 72 KIAS 76 KIAS CAUTION
129. g 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 coded response of pulses to ground based radar on a frequency of 1090 MHz The 73 is equipped with ident capability that activates the Special Position Identification SPI pulse for 18 seconds In addition to displaying the code reply symbol and mode of operation the KT 73 screen will display pressure altitude The displayed pressure altitude may not agree with the aircraft s baro corrected altitude under non standard conditions The Traffic Information Service TIS and Automatic Dependent Surveillance Broadcast ADS B is not available in this installation NOTE The KT 73 owner accepts all responsibility for obtaining the proper license before using the transponder The coverage you can expect from the KT 73 is limited to line of sight Low altitude or aircraft antenna shielding by the aircraft itself may result in reduced range Range can be
130. ght 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 characters the remaining characters on the right side shall be filled with spaces SWITCHING BACK TO DEFAULT 1 2 Press SEL button G to enter the select mode Rotate B to the indication First push on C indicates FN Al DEF inverted Can be set to AIZDEF with STO button CHANGING THE FLIGHT NUMBER Press SEL button G Rotate B until FN is displayed Push C twice to enter the FN editing mode Change the FN as described above 920 8 Page Date 31 January 2006 Pilot s Operating Handbook Section 920 EXTRA 300S XTRA BECKER ATC 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 inverte
131. gines ON OFF After having switched on the AVIONIC MASTER switch the TRT 800 hasto be turned on by hand by pressing the ON OFF button forless then 1 second The display will first show the transponder type and the software and firmware version To turn off the unit the button ON OFF must be pressed for more then two seconds or the AVIONIC MASTER switch must be placed to the OFF position ACS is the default operation mode and the transponder replies to Mode A C and S interrogations The pressure altitude will be displayed as Flight Level SQUAWK SELECTION Squawk selection is done with the four rotating knobs to provide 4096 identification codes The assignments of the knobs starting at top left are X selection of thousands 0 7 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 31 Januar
132. graph 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 GENERAL ER 6 3 AIRCRAFT WEIGHING PROCEDURE 6 3 Owners Weight and Balance 6 4 CENTER OF GRAVITY CALCULATION SAMPLE PROBLEM 6 5 6 7 Weight and Balance Record Sheet 10000 6 7 LOADING WEIGHTS AND MOMENTS ennnen 6 8 WEIGHTS AND MOMENT LIMITS 6 9 EQUIPMENT IST 6 10 Page Date 20 April 2002 6 1 Section 6 Pilot s Operating Handbook Weight and Balance and Equipment List XTRA EXTRA 300S Left blank intentionally 6 2 Page Date 20 April 2002 Pilot s Operating Handbook Section 6 EXTRA 300S 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 airc
133. he 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 to 6 times Then let starter cool for 30 minutes 904 3 EMERGENCY PROCEDURES Not affected 904 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 CAUTION Pay attention to objects and persons in the propeller operating area Hold the canopy tight 8 Apply the brakes 9 Engage starter 10 When engine fires release the ignition switch back to BOTH 11 Pull the external power plug from the board receptacle 12 Move mixture c
134. imply 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 906 4 Page Date 20 April 2002 Pilot s Operating Handbook Z Section 906 EXTRA 300S XTRA Long Range Wing Tank Capacity 906 6 WEIGHT AND BALANCE LOADING WEIGHTS AND MOMENTS TOTAL FUEL CAPACITY 205 LITER 54 1 US GAL AGRO amp CENTER TANK WING TANKS LITER KG KG x CM KG KG x CM US GAL LBS IN LBS LBS IN x LBS 26 72 15 9 238 207 5 3 14 4 31 8 475 412 10 6 288 63 5 950 825 60 15 9 43 2 95 3 1426 1238 80 21 1 57 6 127 0 1901 1650 100 26 4 72 0 158 8 2376 2063 120 31 7 86 4 190 5 2851 2475 140 36 9 100 8 222 2 3326 2888 154 40 6 110 8 244 4 3656 3177 906 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 g
135. 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 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 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 ent
136. isplayed 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 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 CONTRAST This page is only displayed if manual contrast mode is selected in Configuration Mode Contrast is controlled by the 8 and 9 keys DISPLAY This page is only displayed if manual backlighting mode is selected on Configuration Mode Backlighting is controlled by the 8 and 9 keys LIMITATIONS Not applicable Page Date 31 January 2006 914 5 Section 914 Pilot s Operating Handbook GARMIN GTX 327Transponder XTRA EXTRA 3005 914 3 EMERGENCY PROCEDURES 914 3 1 IMPORTANT CODES 7600 Loss
137. itch 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 appears in the bottom line of the LC display E 2 line LC display Code indication top line Codes from 0000 to 7777 are possible Mode indication bottom line SBY mode SbY is displayed Mode A ON appears in the display is displayed the duration of the identification function Mode A C ALT If a valid altitude is present the flight level height in steps of 100 ft preceded by F e g F241 24100 ft appears If no valid altitude code is present 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 an
138. ition 2 Empennage 1 All round inspection canopy surfaces stabilizer elevator trim rudder and tailwheel 2 Horizontal stabilizer attachment bols 3 Right Wing NOOR Aileron freedom of movement and security Trailing edge Fuel tank vent opening right landing gear Fuel quantity Fuel tank filler cap Right landing gear wheel and brake Stall warning vane CHECK CHECK FOR FREEPLAY BY MOVING THE TIP OF THE HORIZ STABILIZER UP AND DOWNWARDS CHECK CHECK CHECK CHECK CHECK CHECK CHECK Page Date 20 April 2002 Pilot s Operating Handbook XTRA Section 4 EXTRA 3005 Normal Procedures 4 Nose 1 Engine oil dipstick CHECK 2 Propeller and spinner CHECK 3 Air inlet CHECK 4 Acro amp center fuel tank drain DRAIN FOR AT LEAST 4 SECONDS TO CLEAR SUMP OF POSSIBLE WATER CHECK CLOSED 5 Wing fuel tank drain DRAIN FOR AT LEAST 4 SECONDS TO CLEAR SUMP OF POSSIBLE WATER CHECK CLOSED 6 Fuel filter drain DRAIN FOR AT LEAST 4 SECONDS TO CLEAR FILTER OF POSSIBLE WATER CHECK CLOSED 7 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 Parachute handling briefing COMPLETE 3 Seat seatb
139. ition Stay close to the downed aircraft to permit easier spotting by airborne searchers A 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 903 4 Page Date 20 April 2002 Pilot s Operating Handbook Section 903 EXTRA 300S 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 gt D REMOVE ELT FROM A C Severed whip antenna cable Danger of fire or explosion in aircraft Temperature extremes aircraft Poor transmitting location i 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 brack
140. itional 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 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 919 4 NORMAL PROCEDURES Not applicable 919 5 PERFORMANCE Not applicable 919 8 Page Date 31 January 2006 Pilot s Operating Handbook TR A EXTRA 300S 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 eect 920 3 Controlsand Indicators Ae cul gast ct 920 4 Switching on the Unit pre flight 920 4 M 920 5 SquawWwKSelec
141. ituations OFF used to de activate transmitter or to insure non activation by 2 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 switch only OFF used to de activate transmitter after automatic activation by the G switch 903 8 HANDLING SERVICING AND MAINTENANCE Visually inspect the unit at regular intervals for cleanliness and secureness Check whip antenna mounting and cable connections for tightness In accordance with FAA regulations batteries must be replaced after 2 years shelf or service life or for any of the following reasons after the transmitter has been used in emergency situation including any inadvertent activation of unknown duration after the transmitter has been operated fore more than one cumulative hour on or before battery replacement date Page Date 20 April 2002 903 7 Section 903 Z Pilot s Operating Handbook Emergency Locator Transmitter X TRA EXTRA 3005 Left blank intentionally 903 8 Page Date 20 April 2002 ict XTRA SECTION 904 EXTERNAL POWER Table of Contents Par
142. iven under following conditions 1 Maximum allowed weight 920 kg 2028 105 except otherwise stated 2 Take off and landing on concrete surface 3 No wind 4 Standard atmospheric condition 5 1 2 Definitions of Terms For definition of terms abbreviations and symbols refer to section 1 General 5 1 3 Sample Problem TAKE OFF CONDITIONS Field Pressure Alt 2000 ft Temperature 15 C Wind Component Headwind 8 KT 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 EXTRA 3005 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 Takeoff 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
143. k Posuit Section 915 EXTRA 3005 GARMIN GTX 330 Transponder 915 1 GENERAL The Garmin GTX 330 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 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 radar 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 transpond
144. l OGOS soe 52500 SMOKE SYSTEM 000000000 oojo CIRCUIT BREAKER BREAKER BREAKER 908 8 HANDLING SERVICING AND MAINTENANCE At every refilling Check automatic shut off Additionally during the 100h Check for the DUAL PUMP SYSTEM Check the system for leakage lines fittings tank Check the smoke oil tank for proper attachment Check the function of the solenoid valve Clean the injector nozzle if required remove carbon debris Additionally during the 100h Check for the SINGLE PUMP SYSTEM Check the system for leakage lines fittings tank Check the smoke oil tank for proper attachment Clean the overpressure check valve if required remove oil residue Clean the injector nozzle if required remove carbon debris Clean the filter element After each flight with activated Smoke System Clean the aircraft belly fairing and the rudder cable from oil slick NOTE The rudder cables might suffer from increased wear when they are covered with smoke oil and dust XTRA Piot s Operating Left blank intentionally Page Date 20 September 200 Pilot s Operating Handbook TR A EXTRA 300S 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
145. l 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 00 On condition you push S1 for another time during this two seconds you get to other submenues else the instrument returns into the Normal Operating Mode All LEDs are illuminated during the submenues 4 DISPLAY OF THE TOTAL EXTREME VALUES Push button twice S1 Reset of the Total Extreme Values Push button twice S1 and once S2 you push S1 twice the LC Display shows the Total extreme values These values are the maximums of positive and negative acceleration that occurred since the last reset of these values They are signed with a B as first charac ter of a line like the following example B 84g B 4 29 In case you want to reset these two values you have to press 52 and the instrument sets the Total extreme values to 0g and returns into the Normal Operating Mode Provided you pushed 51 instead of S2 the LC Display will show the Absolute Extreme Values If there is no button pushed the instrument will return into the Normal Operating Mode 5 DISPLAY OF THE ABSOLUTE EXTREME VALUES push button three times S1 Display of time and date of the Absolute Extreme Values push button three times S1 and once S2 After pushing S1 for three times the LC Display shows the greatest positive and the great est negative acceleration the instrument ever measured These two values a
146. l swivel capability exceeding plus minus 30 deflection The steelsleeve is glued into the glasfiberspring which is bolted to the tail hardpoint of the aircraft The steering of the tailwheel is accomplished by a direct mechanic link rudder control cable from the rudder pedals The steering deflection of the tailwheel is controlled by the rudder movement and dampened by anti shimmy connector springs Page Date 20 April 2002 901 3 Section 901 Pilot s Operating Handbook Steerable Tail Wheel XTRA EXTRA 3005 901 8 HANDLING SERVICING AND MAINTENANCE During 50 hour inspection the bearing steelsleeve has to be lubricated on the point of lubricating Additionally all parts of the tailwheel have to be inspected visually for deforma tions cracks and corrosion 901 4 Page Date 20 April 2002 XTRA SECTION 902 ELECTRIC ACCELEROMETER Table of Contents Paragraph Page 902 1 GENERAL cic 902 3 902 2 LIMITATIONS meo 902 3 902 3 EMERGENCY PROCEDURES 902 3 902 4 NORMAL PROGCEDUBRES 2 1 annue 902 3 902 5 dsiaellUiecme M M 902 3 902 6 WEIGHT AND BALANCE 2 e paa i aiaa 902 3 902 7 DESCRIPTION AND OPERATION OF THE SYSTEM 902 3 902 8 HANDLING SERVICING AND M
147. 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 ThelBIT 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 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 IBIT 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 Dat
148. list may be modified by the minimum equipment requirements of individual certifying authorities 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 7 8 SEATS SEAT BELTS The seat is an ergonomical shaped carbon composite construction It s back rest position and angle is mechanically adjustable on ground by quickpins and bolts The lower seat surface itself is fixed Seat to pedal distance can be varied on ground and in flight using the electrically actuated pedal adjustment system Each pedal can be adjust separate by a switch on the instrument panel 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 separate 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 Page Date 20 April 2002 7 7 Section 7 Nei Pilot s Operating Handbook Description and Operation of Aircraft and Systems X TRA EXTRA 300S 7 9 CANOPY The c
149. n 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 31 January 2006 914 3 Section 914 Pilot s Operating Handbook GARMIN GTX 327Transponder XTRA EXTRA 3005 914 1 2 CODE SELECTION Code selection is done with eight keys 0 7 that provide 4 096 active identification codes Pushing one ofthese keys begins the code selection sequence The new code will notbe activated until the fourth digit is entered Pressing the CLR key will move the cursor back to the previous digit Pressing the CLR key when the cursor is on the first key of the code or pressing the CRSR key during code entry will remove the cursor and cancel data entry restoring the previous code The numbers 8 and 9 are not used for code entry only for entering a Count Down time and in Configuration Mode IMPORTANT CODES 1200 The VFR code for any altitude in the US Refer to ICAO standards elsewhere 7000 The VFR code commonly used in Europe Refer to ICAO standards 0021 The VFR code commonly used in Germany default is set to 0021 at time of installation 7500 Hijack code Aircraft is subject to unlawful interference 7600 Loss of communications 7700 Emergency 7777 Military intercepto
150. ndbook BECKER ATC 4401 Transponder XTRA EXTRA 3005 Left blank intentionally 919 2 Page Date 31 January 2006 Pilot s Operating Handbook E Section 919 EXTRA 300S 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 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 ATC 4401 is equipped with IDENT capability that activates the Special Position Identification SPI pulse NOTE The ATC 4401 owner accepts all responsibility for obtaining the proper license before using the transponder Refer to Becker Pilot s Guide Page Date 31 January 2006 919 3 Section 919 Pilot s Operating Handbook BECKER ATC 4401 Transponder XTRA EXTRA 3005 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 is switched ALT position Mode A C is switched on Rotary coding sw
151. o 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 A 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 Og there will remain a positive and a negative Total Extreme Value in the memory As soon as a Current Extreme Value occurs that is greater than the positive or lower than the negative Total Extreme Value the corresponding Total Extreme Value is exchanged with the Current Extreme Value This is a possibility to store the positive and the negative Total Extreme Value during different actions while the Current Extreme Values are reseted to Og after every single action The Total Extreme Values can be shown or reseted to 00 by pushing the buttons They signed with a B as the first character on every LC Display line The Total Extreme Values only change if one of them is lower than the corresponding
152. o improve pilots view for acrobatic maneuvers a Lexan window is installed in the lower fuselage skin The rear part of the fuselage is covered with Ceconite 102 The upper fuselage body surface is one part from firewall to vertical stabilizer including the correlated canopy frame It consists of a kevlar laminate The canopy frame itself is constructed by carbon laminate The canopy is one part opens to the right and is held in the open position by a belt Emergency jettisonning is achieved by simply unlatching the canopy For additional pilots protection a roll bar is installed behind the pilots seat Page Date 31 January 2006 7 8 Section 7 Nei Pilot s Operating Handbook Description and Operation of Aircraft and Systems X TRA EXTRA 300S 7 3 WINGS The wing is of CRP construction The dual chamber main spar being a 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 To improve surface quality and for protection of the carbon wing shell an outer layer of glass fibre except of the tank area is applied In the area of the wing tanks is a layer of CRP laminate with an incorporated aluminium thread bonded to the metal fuselage structure as means of lightning protection To prevent buckling of the shell plywood ribs are installed These ribs are permanently protected from environmental effects by an
153. 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 is equipped with specific options additional information required for safe operation will be contained in Section 9 Supplements Instrument markings and placards are provided for the acrobatic category only for normal category refer to corresponding limitations This aircraft is certified under 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 SERVICE MANUAL EA 300 S 2 2 AIR SPEED IAS Never Exceed Speed VNE 220 knots Max Structural Cruising Speed VNO 158 knots Maneuver speed Normal VA 140 knots Maneuver speed Acro VA 158 knots 2 3 CROSS WIND COMPONENT Max demonstrated cross wind component for take off and landing 15 knots 2 4 ENGINE Engine type Textron Lycoming AEIO 540 L1B5 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 3005 2 4 1 FUEL Minimum grade aviation gasoline 100 100LL for alternate fuelgrades see latest revision of Lyc
154. om Pilot s Operating Handbook Digital RPM Indicator XTRA EXTRA 300S 905 5 PERFORMANCE Not affected 905 6 WEIGHT AND BALANCE Not affected 905 7 DESCRIPTION OF THE SYSTEM The operation of the indicator is straight forward After power is supplied to the indicator the engine is started and the self tests are 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 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 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
155. on 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 Green 2 e 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 alert 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 905 3 Section 905 i
156. ons 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 authorized service station is allowed to enter or change the ICAO aircraft address If you do not have the ICAO aircraft address Please refer to your national aviation authority to apply for your aircraft address 913 6 Page Date 31 January 2006 Pilot s Operating Handbook 7 Section 913 EXTRA 3005 XTRA FILSER TRT 800 Transponder The Aircraft Identification FID code is displayed on the right bottom line and consists of seven alphanumerical characters CAUTION The ICAO Flight Plan specifies only 7 characters as Flight Identification Filser reserves 8 characters as stated in ED 73B for further expansion of the flight plan The user shall only program 7 characters for FID SELECTING FLIGHT IDENTIFICATION By pressing the button FID for more than 3 seconds the unit will change in
157. ontrol slowly and smoothly to FULL RICH Page Date 31 January 2006 904 3 Section 904 Pilot s Operating Handbook External Power XTRA EXTRA 3005 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 904 5 PERFORMANCE Not affected 904 6 WEIGHT AND BALANCE Not affected 904 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 N N External Power Relais Diode By 550 100 cZ 2 ANS CSE AACE External Power Receptacle AN 2552 3A 12V 28AH Main Relais 8 EE BATTERY T T Master Switch Starter Relais STARTER 904 4 Page Date 31 January 2006 Pilot s Operating Handbook 2 Section 904 EXTRA 300S XTRA External Power 904 8 HANDLING SERVICING AND MAINTENANCE Not affected Page Date 20 April 2002 904 5 Section 904 junii Pilot s Operating Handbook
158. ook up the tow shall be tighened gently During the following take off and climb the maximum air tow speed of the glider must be observed C CLIMB While climbing the max C H T must be observed Towing light gliders the intial climb angle may be very step Information of the glider pilot is recomended D RELEASE After the release of the glider a gently left handed descent shall be flow to avoid collision of glider and air tow Page Date 20 April 2002 Pilot s Operating Handbook Section 907 EXTRA 300S XTRA Airtow Hook E DESCENT AND LANDING While descending the engine temperatures shall be observed Avoid overcooling Final approach should account for the air tow hanging below the aircraft flight path 907 5 PERFORMANCE The existing POH Data remain valid with the exception of TAKE OFF DISTANCE in Meter Conditions Power over 2600 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 1096 CAUTION Maximum permissible air towing speed of the glider needs to be observed Takeoff weight glider 350 Kg Press 10 0 OAT alti
159. ould 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 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 Page Date 20 April 2002 4 11 Section 4 2 Pilot s Operating Handbook Normal Procedures XTRA EXTRA 300S 4123 SPIN To enter a spin proceed as follows Reduce speed power idle When the plane stalls kick rudder to desired spin direction hold ailerons neutral stick back positive spinning Stick forward negative spinning The plane will immediately enter a stable spin Ailerons against spin direction will make the spin flatter Ailerons into spin direction will lead to a spiral dive Above apply for positive and negative spinning To stop the spin Apply opposite rudder Make sure power idle Hold ailerons 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
160. our Position rotary switch IOFF 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 orange with dimmer Lights up if transponder responds intensity set by means of a mechanical dimmer 4 coding switches Rotary switches with eight Setting the code from 0000 to 7777 permitting positions 4096 different digit combinations Code readout Digital readout each digit Indication of coding from 0000 to 7777 from 0 to 7 Page Date 31 January 2006 918 3 Section 918 Pilot s Operating Handbook BECKER ATC 2000 Transponder XTRA EXTRA 3005 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
161. parate independent tanks Acro amp Center tank in the fuselage Wing tank LH and RH Wing tank The root section of each wing in front of main spars forms an integral fuel tank providing two interconnected tanks with 120 liters 31 7 US GAL total capacity Each side of the wing has a 2 diameter filler cap for gravity refueling The wing tank can be completely emptied in flight but the normal amount of unusable fuel is approximately 2 Liters 0 5 US Gallon Acro amp center tank An Acro tank 9 liters 2 3 US Gal is mounted in the fuselage just behind the firewall and the Center tank 42 liters 11 1US Gal just behind the main spar of the wing The Acro tank is connected with the center tank in a gravity feed system The center tank has a 2 diameter filler cap for gravity refueling Unusable fuel is approximately 2 liters 0 5 US Gal Adequate venting is provided in each tank to a main ventilation tube ending outside the fuselage at the right side In addition to the engine driven fuelpump an electrically driven auxiliary fuel pump boost pump with by pass and having sufficient capacity to feed the engine at take off power is fitted as a safety device against failure of the engine driven pump The boost pump switch is located on the instrument panelt A fuel filter with drain is installed between the fuel selector valvef and the boost pump Separate drains are located at the lowest point of each tank system Normal floa
162. propeller is automatically adjusted to coarse pitch in order to avoid overspeeding The use of 100 130 aviation grade fuel AVGAS 100 100LL is the minimum grade recommended by the manufacturer of the engine For continuous operation 115 145 aviation fuel is the maximum grade 7 8 Page Date 31 January 2006 Pilot s Operating Handbook Section 7 EXTRA 300S X TRA Description and Operation of Aircraft and Systems 7 10 2 7 10 3 7 10 4 7 10 5 7 10 6 7 10 7 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 Oil capacity Max sump capacity 16 qts Min sump capacity Acro 12 Normal 9 gts For temperatures and oil grades refer to Section 1 7 ENGINE INSTALLATION The engine is mounted with four shock mounts Type LORD or BARRY CONTROLS to the tig welded steel tube engine support 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 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 PROPELLER The propeller is a 4 blade wood composite
163. ptional equipment marked as such 9 9 09 9 9 0 9 0 009 59 69 9 798 0969 Standard Optional Position Item Magneto Selector Switch amp Starter Amperemeter Altimeter Air Speed Indicator Manifold Pressure Fuel Flow Magn Direction Indicator Oil Pressure Oil Temperature G Meter EGT CHT RPM Indicator COM Fuel Quantity Center Tank Fuel Quantity Wing Tank Master Switch Field Switch Low Voltage Monitor Boost Pump Switch Nav Light Switch Strobe Light Switch Radio Master Switch Left Pedal Adjustment Switch Right Pedal Adjustment Switch Circuit Breaker Stall Warninig Circuit Breaker Alt Field Circuit Breaker Alt Output Circuit Breaker Starter X X X X X X X X X X X X X X X X X X X X X X X X X X 7 6 Page Date 20 April 2002 Pilot s Operating Handbook Section 7 EXTRA 300S X TRA Description and Operation of Aircraft and Systems Standard Optional Position Item Circuit Breaker Boost Pump Circuit Breaker Nav Lights Circuit Breaker Strobes Circuit Breaker Radio Circuit Breaker Fuel amp RPM Gauges Circuit Breaker Pedal Adjustment RPM control Prop governor Mixture control Throttle lever Stick Radio button Fuel shutoff valve Trim lever and indicator Turn amp bank indicator GPS X X X X X X X X X X X X X NOTE This
164. r 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 screen The word IDENT will appear in the upper left corner of the display while the IDENT mode is active VFR Sets the transponder code to the pre programmed VFR code selected in 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 31 January 2006 Pilot s Operating Handbook E Section 914 XTRA GARMIN GTX 327 Transponder EXTRA 300S 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 d
165. raft 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 N XG distance fire wall Center of Gravity W1 Sum of weights indicated by the two scales below the main wheels We Weight indicated by the scale below the tail wheel W Total weight W1 W2 XG 1 x X1 W2 x X2 C G position W Reference Firewall plane W W1 W2 XG W1 x X1 W2 x X2 W Page Date 31 January 2006 6 3 Section 6 Weight and Balance and Equipment List XTRA Pilot s Operating Handbook EXTRA 300S 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 XG Wo Wn W 6 2 1 Owners Weight and Balance Record Wo x Xo Wn x Xn C G position Enter below all weight change data from aircraft log book EXTRA 300 S SERIAL NUMBER REGISTRATION Date Description of Weight change Running empty modification Added Removed weight Wt kg Arm cm
166. ransponder 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 76 If no faults are detected the reply light illuminates 916 2 LIMITATIONS Not Applicable 916 3 EMERGENCY PROCEDURE IMPORTANT CODES 7500 Use to report a hijacking 7600 Signifies communication failure 7700 Reserved for emergencies 916 4 Page Date 31 January 2006 Pilot s Operating Handbook 2 Section 916 EXTRA 3005 XTRA BENDIX KING KT 76A Transponder 916 4 NORMAL PROCEDURE After engine start up turn the function selector to the Standby SBY position Then select the proper reply code by rotating the code select knobs As soon as aircraft is airborne switch the function selector to ON Your KT 76A is now operating in Mode or normal mode To operate in or altitude reporting mode turn the function selector to ALT if aircraft is equipped with altitude encoding equipment 916 4 1 SQUAWK IDENT When you are asked to ident by ATC briefly press the IDENT push button Your aircraft will be positively identified to the Air Traffic Controller 916 5 PERFORMANCE Not Applicable Page Date 31 January 2006 916 5 Section 916 mE Pilot s Operating Handbook BENDIX KING KT 76A Transponder XTRA EX
167. ravity 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 906 8 HANDLING SERVICING AND MAINTENANCE Not affected Page Date 20 April 2002 906 5 Section 906 Z Pilot s Operating Handbook Long Range Wing Tank Capacity XTRA EXTRA 300S Left blank intentionally 906 6 Page Date 20 April 2002 Pilot s Operating Handbook XTR A EXTRA 3005 Paragraph 907 1 907 2 907 3 907 4 907 5 907 6 907 7 907 8 SECTION 907 AIRTOW HOOK Table of Contents Page GENERAL 907 3 LIMITATIONS sme 907 3 EMERGENCY 5 e ras 907 4 NORMAL PROCEDURES ratum anat dads Ruin 907 4 PERFORMANCE 907 5 WEIGHT AND BALANCE eran 907 7 DESCRIPTION OF THE SYSTEM 907 7 HANDLING SERVICING AND MAINTENANCE 444 1222 907 7 Page Date 20 April 2002 907 1 Section 907 Pilot s Operatin
168. re rescue cerunt 3 4 3 2 1 Engine Failure during Take off Roll nennen 3 4 3 2 2 Engine Failure immediately after 3 4 3 2 3 Engine Failure during Flight Restart Process 3 4 3 2 4 Oil System a 3 5 3 2 5 3 5 3 3 FORCEDILANBINGS o 3 5 3 3 1 Emergency Landing without Engine 3 5 3 3 2 Precautionary Landing with Engine 2 eene een 3 5 3 4 3 6 3 4 1 During Start on 3 6 3 4 2 If E gine Falls onc Dude vide aoe dete ene 3 6 3 4 3 Frein sed 3 7 3 5 nee 3 7 3 5 1 Inadverted Ernicouhtetr boats chev ble 3 7 3 6 UNINTENTIONAL SPIN 3 7 3 7 LENIIPTBISTELeULEE 3 7 3 8 EMERGENCY EXIT AFTER TURN OVER nennen nnne 3 8 3 9 ELEVATOR CONTROL FAILURE eseeeeeeseeeeee nennen nenne nnn nnnm n nnn tn snas ntn nass antra nnn 3 8 Page Date 20 April 2002 3 1 Section 3 Emergency Procedures XTRA Pilot s Operating Handbook EXTRA 300S Left blank in
169. re stored in the long term memory of the instrument and signed with a C as first character of the LC Display 9 69 C 83g Page Date 20 April 2002 902 7 Section 902 Pilot s Operating Handbook Electronic Accelerometer XTRA EXTRA 300S Additionally the long term memory stores the times and dates when new Absolute Extreme Values occur They are shown if you push S2 next In this case during the next twelve seconds the LC Display shows under the title MAX DATE the time and date of the posi tive 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 four times S1 The LC Display will exhibit time and date after you have pushed S1 for four times For example 02 52 PM 12 09 93 is the ninth December 1993 at 2 o clock and 52 minutes in the afternoon If you want to set the clock you have to push 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 I
170. stem 7 5 Flight Control Systems ioi cauia te eae 7 5 Directional Flight Control System 7 5 Secondary Control es 7 5 INSTRUMENTATION 7 5 Instrument Panel 7 6 LANDING GEAR E 7 7 SEATS SEAT BELTS 0 A 7 7 GANOP V EE 7 8 POWER 7 8 ENGINE 7 8 IES I AREE TEE 7 9 Engine M 7 9 7 9 7 9 juam 7 9 RPM Conthol 2 dungen die ete 7 9 Fuel Selector 7 10 Exhaust Systems eae duds 7 10 US VS TE uenerit num A 7 10 ELECTRICAL SYSTEM 7 11 CABIN ENVIRONMENT CONTROL seen nnn nnne nn annia nasa nnn ansia nina 7 13 Page Date 31 January 2006 741 Section 7 Pilot s Operating Handbook Description and Operation of Aircraft and Systems XTRA EXTRA 300S Left blank intentionally 7 2 Page Date 20 April 2002 Pilot s Operating Handbook
171. t type transducers and electrically operated fuel indicators are used 7 10 Page Date 31 January 2006 Pilot s Operating Handbook Section 7 EXTRA 300S X TRA Description and Operation of Aircraft and Systems 7 12 ELECTRICAL SYSTEM The electrical power generation system consists of a 12 V alternator with rectifier and transistor voltage regulator The alternator is mounted on and driven by the engine The field current is controlled by the voltage regulator to give a nominal output of 13 8 V under all load conditions Circuit protection against over voltage is provided by the voltage regulator The maximum load taken from the alternator is 40 amp The system is equipped with a low voltage monitor that gives a visual warning if the aircraft voltage drops below 12 75 V The master switch is located on the instrument panel 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 instrument panel and they are easily accessible to the pilot during flight The electrical system is adequately suppressed to ensure satisfactory operation of the radio equipment All wires switches circuit breakers etc are manufactured to related aeronautical specifications
172. tentionally Page Date 20 April 2002 Pilot s Operating Handbook Section 3 EXTRA 300S XTRA Emergency Procedures SECTION 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 pilot and or aircraft Thorough knowledge of these procedures will enable the pilot to better cope with an emergency The steps should be performed in the listed sequence However the procedures do not restrict the pilot 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 In any emergency situation contact should be established with a ground station as soon as possible after completing the initial corrective action Include position altitude heading speed nature of the emergency and pilot s intentions in the first transmission There after the ground station should be kept informed of the progress of the flight and of any changes or developments in the emergency Three basic rules apply to most emergencies and should be observed by each aircrew member 1 Maintain aircraft control 2 Analyze the situation and take proper ac
173. 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 SMOKE REFILL SMOKE CONTROL mo Goss BREAKER B SINGLE PUMP SYSTEM The smoke oil tank is filled by a pump reversed polarity through a quick connector located in the aircraft belly fairing This line includes a filter to prevent dirt to enter the smoke system A filled smoke oil tank is detected by a float switch placed in the tank which shuts the pump off The same pump normal polarity injects the smoke oil from the smoke oil tank through an overpressure check valve and the injector nozzle into the hot exhaust gas to generate smoke 508 6 Page Date 20 September 200 o XTRA um The system consists of Floptube smoke oil tank with float switch Refill Injection pump in the pilot compartment with quick connector in the belly fairing Overpressure check valve in smoke oil supply line to the nozzle Filter element in the refill line ON OFF switch on the throttle lever Tworelais changeover contact type for pump control SMOKE ARM switch to arm the system and SMOKE REFILL switch for refilling placed at the instrument panel Only 1 circuit breaker for pump and control placed at the instrument pane
174. tiohns eene nennen nennen nennen eren enses 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 ACIVation 2 N 920 10 Configuration Mode 2 4204424 0 00 enn 920 10 LIMITATIONS 920 10 EMERGENCY PROCEDURES 920 10 Important CodeS 920 10 NORMAL PROCEDURES siisii ieena aa aa aeaa aaae aK a auaa 920 10 usen huigu7 920 10 Page Date 31 January 2006 920 1 Section 920 mE Pilot s Operating Handbook BECKER ATC 6401 Transponder XTRA EXTRA 3005 Left blank intentionally 920 2 Page Date 31 January 2006 Pilot s Operating Handbook 7 Section 920 EXTRA 3005 XTRA BECKER ATC 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
175. tion 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 X TRA EXTRA 3005 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 cat 920 kg 2028 LBS 90 KIAS Acrobatic cat 820 kg 1808 LBS 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 Pull amp Turn 4 Ignition switch OFF 5 Master switch OFF 6 Forc
176. to 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 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 line Additionally the result of the internal analysis are displayed in the second line LIST OF POSSIBLE ERRORS 1 ANT will appear if the antenna is defective e g broken cable 2 FLerr instead of the altitude appears on the display if there is an error with the altimeter or if the aircraft is outside the altitude range FL 010 to FL350 If the mode ACS was active before it will change to mode A S automatically 3 DC for a faulty transmitter power supply 4 FPG for
177. 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 ofthese keys begins the code selection sequence The new code will notbe activated until the fourth digit is entered Pressing the CLR key will move the cursor back to the previous digit Pressing the CLR key when the cursor is on the first key of the code or pressing the CRSR key during code entry will remove the cursor and cancel data entry restoring the previous code You may press the CLR key up to five seconds after code entry is complete to return the cursor to the fourth digit The numbers 8 and 9 are not used for code entry only for entering a Count Down time contrast and display brightness and in the Configuration Mode IMPORTANT CODES 1200 The VFR code for any altitude in the US Refer to ICAO standards elsewhere 7000 The VFR code commonly used in Europe Refer to ICAO standards 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
178. tude T O 50 ft T O 50 ft T O 50 ft T O 50 ft T O 50 ft T O 50ft Takeoff weight glider 600 Kg Press 10C ONT altitude T O 50 ft T O 50 ft T O 50 ft T O 50 ft T O 50 ft T O 50ft Takeoff weight glider 765 Kg Press 10 C OAT altitude T O 50 ft T O 50ft T O 50ft T O 1508 T O 50ft T O 50 ft Page Date 20 April 2002 907 5 Section 907 ind Pilot s Operating Handbook Airtow Hook XTRA EXTRA 300S CLIMBRATE Conditions Power 2500 Rpm and full throttle mixture rich Speed of the aircraft tow 76 KIAS 140 Km h Weight of the towing aircraft m 820 Kg 1808 Ib 1 Pilot 86 kg Acro amp Center Tank full 38 L Wingtank 30 L Tow force glider with 350 Kg 0 1000 ft 2000 ft 3000 ft 4000 ft 5000 ft 6000 ft 7000 ft 8000 ft Tow force glider with 600 Kg 0 ft 1000 ft 2000 ft 3000 ft 4000 ft 5000 ft 6000 ft 7000 ft 8000 ft Tow force glider with 765 Kg 0 ft 1000 ft 2000 ft 3000 ft 4000 ft 5000 ft 6000 ft 7000 ft 8000 ft 907 6 Page Date 20 April 2002 Pilot s Operating Handbook Section 907 EXTRA 300S XTRA Airtow Hook 907 6 WEIGHT AND BALANCE Not affected 907 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 c
179. turer Textron Lycoming Williamsport Plant PA 17701 USA a Type Lycoming AEIO 540 L1B5 b Type Lycoming AEIO 540 L1B5D Rated power 300HP 2700RPM 270HP 2400RPM PROPELLER Manufacturer MT Propeller Entwicklung GmbH Federal Republic of Germany MTV 9 B C C 200 15 3 blade constant speed Type MTV 14 B C C 190 17 4 blade constant speed 1 5 1 Exhaust Systems Optional 1 6 1 7 FUEL OIL Manufacturer Gomolzig Flugzeug und Maschinenbau GmbH Federal Republic of Germany Exhaust Silencer for standard system PN EA 300 NSD GO3 606500 Complete 6 in 1 System with integrated Silencer PN EA 300 606000 Fuel type AVGAS 100 100 LL for alternate fuel grades see later issues of Textron Lyc S l No 1070 Minimum 100 130 octane Maximum 115 145 octane Total fuel volume 171 litres 45 1 US Gallon Wingtanks 2 x 601 120 litres 31 7 US Gallon Center tank 42 litres 11 1 US Gallon Acro tank 9 litres 2 3 US Gallon Usable fuel in the system 169 litres 44 6 US Gallon Usable fuel for acrobatic acro and center tank 49 litres 12 9 US Gallon Maximum sump capacity 16 qts Minimum sump capacity Acrobatics 12 qts Normal 9 gts Average ambient air Mil L6082 Mil 22851 temperature grades ashless dispersant grades All temperatures SAE 15W50 20W50 gt 27 80 F SAE 60 SAE 60 gt 16 C 60 F SAE 50 SAE 40 or 60 1 C til 32 C SAE 40 SAE 40 30 F 90 F
180. ugzeug produktions und Vertriebs GmbH LBA approval The editor has the copyright of this Flight Manual and is responsible for edition of revisions amendments and supplements 2 4 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 Shouldthis Flight Manual getlost 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 31 January 2006 0 3 Section 0 mE Pilot s Operating Handbook Publication Guidance XTRA EXTRA 300S 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 gt An operating procedures technique etc which is considered essential to emphasize Shall
181. uthority 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 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 7 Descriptions and Operation Page Date 20 April 2002 8 3 Section 8 2 Pilot s Operating Handbook Handling Servicing and Maintenance XTRA EXTRA 300S 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
182. utput 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 902 3 Section 902 iom Pilot s Operating Handbook Electronic Accelerometer XTRA EXTRA 300S The other output display are twentyfive LEDs which are arranged in a semicircle The upper twelve LEDs show positive acceleration the lower twelve LEDs show negative acceleration The middle LED is on line all time long INSTANTANEOUS ACCELERATION The current value of acceleration is called Instantaneous Acceleration It is shown by the LED display if the value is between 12g and 129 the Instantaneous Acceleration is zero g only the middle LED lights up Every single g illuminates one more LED in positive up or negative down direction For example The Instantaneous Acceleration is 5g the middle LED and five LEDs in positive direction are illuminated If the Instantaneous Acceleration is 7g the middle LED and seven LEDs in negative direction are illuminated In case the absolute value of the Instantaneous Acceleration is greater then 12g all twelve LEDs of this range are turned on CURRENT EXTREME VALUES A permanent illumination of two LEDs one for positive acceleration and another one for negative acceleration shows the Current Extreme Values They are signed by tw
183. ws 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 Displa 52 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 Og The LCD shows A 0 0g 0 09 After two seconds the Instrument changes automatically into the Normal Operating Mode 2 THE NORMAL OPERATING MODE In the Normal Operating Mode the instrument outputs the Instantaneous Acceleration and the Current Extreme Values The Instantaneous Acceleration is shown as a bar on the LED Display Furthermore one LED indicates the positive and another one indicates the negative Current Extreme Value The Current Extreme Values are also shown on the LC Display and signed with an A for Example 7 39 3 59 902 6 Page Date 20 April 2002 Pilot s Operating Handbook Z Section 902 EXTRA 300S 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 al
184. y 2006 912 5 Section 912 Pilot s Operating Handbook FILSER TRT 600 Transponder XTRA EXTRA 300S 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 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 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
185. y 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 S 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 altitude 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 31 January 2006 Pilot s Operating Handbook Section 917 EXTRA 300S XTRA BENDIX KING KT 76A Transponder 0021 The VFR code commonly used

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