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PILOT INFORMATION MANUAL [Last Updated on

1. eene ea ee eke eke nnne 8 p 9 2 Page Date 22 April 2015 Pilot s Operating Handbook Section 9 EXTRA 300LT XTRA Supplements 9 SUPPLEMENTS 9 1 Introduction Section 9 Supplements of the Pilots Operating Handbook contains all information neces sary for a safe and efficient operation of the airplane when equipped with one or more of the various optional systems and equipment not provided with the standard airplane 9 2 Notes The described systems and equipment are certified by the EASA for the EXTRA 300LT Pages and contents of this section must not be exchanged and alterations of or additions to the approved contents must not be made without the EXTRA Flugzeugproduktions und Vertriebs GmbH EASA approval The editor has the copyright of these Supplements and is responsible for edition of revisions The log of effective pages is found on the preceding pages of this Pilot s Operating Handbook Each Supplement section e g steerable tailwheel covers only a single system device or piece of equipment 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 operat
2. 921 4 Page Date 31 May 2012 Pilot s Operating Handbook Section 921 EXTRA 300LT XTRA AIRPLANES REGISTERED IN BRAZIL 921 8 HANDLING SERVICING AND MAINTENANCE Not affected Page Date 31 May 2012 921 5 Section 921 Pilot s Operating Handbook AIRPLANES REGISTERED IN BRAZIL XTRA EXTRA 300LT Left blank intentionally 921 6 Page Date 31 May 2012 Pilot s Operating Handbook X TRA EXTRA 300LT Paragraph 922 1 922 2 922 2 1 922 2 2 922 2 3 922 2 4 922 2 5 922 2 6 922 2 7 922 3 922 3 1 922 3 2 922 4 922 5 922 6 922 7 922 7 1 922 7 2 922 7 3 922 7 4 922 7 5 922 7 6 922 7 7 922 7 8 922 7 9 922 8 SECTION 922 GARMIN GTN 635 650 750 Table of Contents Page GENERAL eege 922 3 LIMITATIONS ca EE EE EEN 922 3 gris ME RE A 922 5 Be E 922 5 ME RE RR EE N 922 5 Taffie lis only ss EE De EE ade 922 5 Flight Planning Calculation Functions sissioni aidaa ee ee rana 922 5 E ME N A N EE 922 6 Demo ModE 922 6 EMERGENCY ABNORMAL PROCEDURES se eek Rees ee eese ener nenne nannten nn 922 6 Emergency lee ME 922 6 Abnormal Procedures i e ee ee oe ee Eheu edo Ehe ee Be tue ru LE Rae pe A es 922 6 NORMAL PROCEDURES cota 922 7 PERFORMANCE EE 922 7 WEIGHT amp CENTER OF GRAVITY cintia 922 8 SYSTEM DESCRIPTION 2 202 ccaer re iaa uoo cenare
3. Page Date 6 April 2010 4 9 Section 4 Pilot s Operating Handbook Normal Procedures XTRA EXTRA 300LT 4 12 ACROBATIC MANEUVERS 4 12 1 GENERAL NOTE Prior to executing these maneuvers tighten harnesses and check all loose items are stowed Start the maneuvers at safe altitude and maximum continuous power setting if not otherwise noted For maneuver limits refer to Section 2 LIMITATIONS After termination of acrobatic maneuvers the artificial horizon if installed must be reset if possible At high negative g loads and zero g periods it is normal that oil pressure and RPM indication might drop down momentarily returning to normal status at positive g loads AN WARNING The high permissible load factors of the airplane may exceed the individual physiological limits of pilot or passenger This fact must be considered when pulling or pushing high g s 4 12 2 MANEUVERS N CAUTION Particular caution must be exercised when performing maneuvers at speeds above V 160 KIAS 296 km h Large or abrupt control inputs above this speed may impose unacceptably high loads which exceed the structural capability of the aircraft Acrobatics is traditionally understood as maneuvers like loop humpty bump hammerhead turn aileron roll etc This manual does not undertake to teach acrobatics however itis meant to demonstrate the plane s capabilities Forthis reason maneuvers are divided into segments The segments
4. Page Date 6 April 2010 917 3 Section 917 Pilot s Operating Handbook ASPEN EFD1000 500 System XTRA EXTRA 300LT This supplementis written for MAP SOFTWARE RELEASE 2 4 1 and IOP SOFTWARE RELEASE 2 0 2 and is not suitable for earlier software versions Some differences in operation may be observed when comparingthe information inthis supplementto later software versions Verify the information herein depending on the configuration installed with the EFD1000 PFD and or EFD1000 500 MFD Pilot s Guide s Doc 091 00005 001 A and or 091 00006 001 and orthe Evolution Synthetic Vision Pilot s Guide Supplement Doc 091 00032 001 B you received with your unit s Additional information can be found in these documents as well 917 1 1 EQUIPMENT CONFIGURATION The table below shows the various possible configurations of Aspen equipment for the 300LT Refer to the Equipment Listin Section 6 to verify which configuration is actually installed in your aircraft Figure 1 provides a block diagram of a complete EFD1000 500 System installation ptf x fof fe OI 917 2 LIMITATIONS This supplement does not grant approval for IFR operations The Aspen flight displays have been installed on a no hazard no credit basis Therefore the information provided by these instruments shall not be relied upon for operation of the aircraft as well as for navigational purposes The navigation data incl for final approach segments provided by
5. 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 pilotingtechniques 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 1096 or more in range and endurance Therefore it is important to utilize all available information to estimate the fuel required for the particular flight Performance Charts Performance data are presented in tabular or graphical form to illustrate the effect of different 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 except otherwise stated The performance figures below are given underfollowing conditions 1 Maximum allowed weight 950 kg 2095 lbs except otherwise stated 2 Take off andlanding on concrete surface 3 Nowind 4 Standard atmospheric condition Definitions of Terms For definition of terms abbreviations and symbols refe
6. On instrument panel above circuit breaker row On instrument panel BREAKER below circuit breaker row 907 3 EMERGENCY PROCEDURES FAILURE OFTHESMOKE SYSTEM 1 Switch SMOKE ARM and SMOKE REFILL OFF 2 Circuit breaker PULL Page Date 18 June 2013 907 3 Section 907 Pilot s Operating Handbook Smoke System XTRA EXTRA 300LT FIRE IN FLIGHT 1 Switch SMOKE ARM OFF N CAUTION If the fire after the smoke system is shut off will not extinguish proceed as follows 2 Mixture IDLECUTOFF 3 Fuel selector valve OFF Pull amp Turn 4 Battery switch OFF 5 Airspeed 100 KIAS 185 km h find your airspeed attitude that will keep the fire away from the cockpit 6 Land AS SOON AS POSSIBLE 7 If fire persists or aircraft is uncontrollable and wearing a parachute BAILOUT SMOKE IN THE COCKPIT 1 Switch SMOKE ARM OFF 2 Bad weather window OPEN 3 Ventilation OPEN 4 If smoke persists in the cockpit land AS SOON AS PRACTICAL 907 4 NORMAL PROCEDURES The smoke system includes features for refilling the smoke tanks and smoke generation A REFILL A separate refill hose is delivered with the smoke system which has to be used for filling the smoke oil tanks from the paraffin oil supply cansister or barrel 1 Refill hose CONNECT hose nipple to quick connector at the fuselage bottom IMMERSE the other end into the paraffin oil in the canister barrel 2 Switch SMOKE REFILL ON
7. Remove quick pins from the backrest adjustment and swivel the backrest forward to get access to the ELT unit Usethe unit master switch at the ELT unit analogously FUNCTION CHECK OF THEELT Ifthe aircraft receiver is operable listen on 121 5 MHz for ELT transmission Ensure thatthe antenna is clear of obstruction 909 4 NORMAL PROCEDURES Notaffected 909 5 PERFORMANCE Not affected 909 6 WEIGHT amp CENTER OF GRAVITY Refer to the equipment list in Section 6 of this Handbook 909 4 Page Date 6 April 2010 Pilot s Operating Handbook Section 909 EXTRA 300LT XTRA ARTEXME 406 ELT 909 7 SYSTEMDESCRIPTION The ELT installation consists of the ELT unit and a buzzer both fastened to the fuselage structure aft of the back seat an antenna located on the main fuselage coverbeh nd the cockpit and a remote switch with LED indication located on the instrument panel The switch hasthe positions ARM and ON 909 7 1 SWITCH OPERATION Inacrash an acceleration activated crash sensor G switch turns the ELT on automatically when the ELT experiences a change in velocity or deceleration of 4 5 fps 0 5 fps Activation is also accomplished by means of the cockpit mounted remote switch or the switch on the ELT To deactivate the ELT set either switch to the ON position then back to ARM The ELT does not have an OFF position Instead a jumper between two pins on the front D sub connector mustbein
8. near the airspeed indicator The markings and placards installed in this airplane contain operating limitations which must be complied with when operating this airplane in the acrobatic category Other limitations that 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 limitations must be observed in the rear cockpit This airplane is certified for VFR day operation Operation under known icing conditions prohibited on the rear instrument panel FUEL AVGAS 100 100LL near each filler cap on the seperate hatch of the upper cowling prt S oo On the rear instrument panel on the trim LED indicator Page Date 6 April 2010 2 9 Section 2 Pilot s Operating Handbook Limitations XTRA EXTRA 300LT FUEL SELECTOR VALVE WING TANKS usable 142 L 37 5 US GAL CENTER 10 10 TANK usable 67 L 17 7 US GAL in both cockpits next to the fuel selector WING TANK MUST BE EMPTY FOR ACROBATICS USABLE FUEL 142L 37 5 US GAL On the rear instrument panel beneath wing tank fuel capacity indicator CENTER TANK INDICATION SHOWS ZERO IN LEVEL FLIGHT BELOW 9 L 2 4 US GAL UNUSABLE FUEL 2 L 0 5 US GAL On the rear instrument panel beneath center tank fuel capacity indicator THE REMAINING FUEL IN LEVEL FLIGHT CANNOT BE USED SAFELY WHEN INDICATOR READS ZER
9. 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 heighte g lifting the canister The fully filled status is sensed by the floating device which automatically switches the refilling off After automatic refill shut off 3 Switch SMOKE REFILL OFF 4 Refill hose DISCONNECT 907 4 Page Date 6 April 2010 Pilot s Operating Handbook Section 907 EXTRA 300LT X TRA Smoke System PN CAUTION A shut off failure of the refill process can be recognized by smoke oil spilling out of the vent line In this case turn off refill switch The floating device switch in the main smoke oil tank has to be checked accordingly B SMOKE GENERATION 1 Bad weather window and ventilation CLOSE 2 SMOKE ARM Switch ON 3 Manifold Pressure minimum 20 Hg 4 Switch in the throttle lever forsmoke generation ON OFF NOTE It is recommended to operate the smoke system only in forward flight because during reverse maneuvers for example tail slide smoke might enter the cockpit via the air vents 907 5 PERFORMANCE Notaffected 907 6 WEIGHT AND BALANCE as se pecific Weight of the paraffin oil 0 85 kg Litre NOTE The smoke system does not feature a capacity dipstick In the case of unknown filling the smoke oil tanks should be drained
10. 1 67 Liters 5 96 Liters Distance to Climb 5 71 1 19 nm 4 52 nm CRUISE Cruise Altitude and Power Setting should be determined for most economical fuel consumption and several other considerations 5 11 shows the Cruise Performance data for a T O Weight of 950 kg 2095 lbs with maximum fuel 209 L The conditions in the examples of the following Figures are Pressure altitude 8000 ft 2438 m Power Setting 65 96 5 8 shows the range 562 nm 1041 km 5 9 shows the endurance 3 3h 5 10 shows the cruise speed 173 kts 320 km h The desired total distance in this sample problem is well within this value DESCENT 5 12 shows Descent Time Distance and Fuel data Example descent from 8000 ft 2438 m to 2000 ft 610 m Time to Descent 8 2 min 6 min Distance to Descent 21 5 NM 16 nm Fuel to Descent 4 1 Liters 3 Liters 0 79 US Gal 5 4 Page Date 6 April 2010 Pilot s Operating Handbook Section 5 EXTRA 300LT XTRA Performance LANDING 5 13 shows the Landing Distance Example Landing Weight 870 kg 1918 lbs Ground Roll 202 m 663 ft decreased by 15 due to headwind 171 m 561 ft Total Distance to clear a 50 ft obstacle 618 m 2028 ft decreased by 15 due to headwind 525 m 1722 ft These distances are well within the available field length in this sample problem 5 2 ISA CONVERSION ISA Conversion of pressure altitude and outside airtemperatu
11. 4 Flashes 5 Flashes 6Flashes 7 Flashes e f this error code persists there may be a problem with the antenna installation This can be checked with a VSWR meter Check the antenna for opens shorts resistive ground plane connection Low power detected Occurs if output power is below about 33 dBm 2 watts for the 406 signal or 17 dBm 50 mW for the 121 5 MHz output Also may indicate that 406 signal is off frequency For this error code the ELT must be sent back for repair orreplacement Indicates that ELT has not been programmed or is incorrectly programmed Does notindicate erroneous or corrupted programmed data Indicates that the G switch loop between pins 5 and 12 at the D sub connector is not installed ELT will not activate during a crash Check that the harness D sub jumper is installed by verifying less than 1 ohm of resistance between pins 5 and 12 Indicates that the ELT battery has too much accumulated operation time gt 1hr see below Battery may still power ELT however it must be replaced to meet FAA specifications May also indicate damage to the battery circuit Page Date 6 April 2010 909 7 Section 909 Pilot s Operating Handbook ARTEXME 406 ELT XTRA EXTRA 300LT Left blank intentionally 909 8 Page Date 6 April 2010 Pilot s Operating Handbook X TR A EXTRA 300LT Paragraph 910 1 910 1 1 910 2 910 3 910 4 910 5 910 6 910 7 910 7 1 910
12. INFORMATION MANUAL EXTRA 300LT MANUFACTURER EXTRA Flugzeugproduktions und Vertriebs GmbH Flugplatz Dinslaken 46569 H nxe Federal Republic of Germany WARNING This is an Information Manual and may be used for general purposes only This Information Manual is not kept current It must not be used as a substitute for the official FAA EASA Approved Pilot s Operating Handbook required for operation of the airplane Left blank intentionally Pilot s Operating Handbook EXTRA 300LT XIRA LOG OF REVISIONS Dates of issue for original and revised pages Origiriall RR RE HE Seed 6 April 2010 Revision No 1 aene 31 May 2012 Revision No 2 assesseer 6 November 2012 REVISION INO 3 eege etes 18 June 2013 Revision No A 22 April 2015 Date and sign of approval EASA MAJOR CHANGE APPROVAL 10030180 Date of Approval sssrini 1 June 2010 Approved underthe authority of DOA N EASA 21J 073 ANAC Validation Process EASA Project N 0010017605 Date of Approval 8 October 2012 EASA MAJOR CHANGE APPROVAL 10045828 Date of Approval ss ssssisssiiianis 22 July 2013 Approved under the authority of DOA N EASA 21J 073 Date of Approval 24 October 2013 Approved underthe authority of DOA N EASA 21J 073 Date of Approval s ssrsnasiire 22 April 2015 Page Date 22 April 2015 X TR A Pilot s EE LOGOFEFFECTIVEPAGES Page Date Page Date M m 6 Ap
13. Music Bass level Music balance RX Balance RX volume level CS Balance CS Bass level LIMITATIONS STEREO STEREO p HEADSET ONLY HEADSET ONLY Next to the front audio sockets Next to the rear audio sockets Page Date 6 April 2010 910 3 Section 910 Pilot s Operating Handbook NAT AA83 001 Intercom XTRA EXTRA 300LT 910 3 EMERGENCY PROCEDURES Not applicable 910 4 NORMAL PROCEDURES Not applicable 910 5 PERFORMANCE Not applicable 910 6 WEIGHT AND BALANCE Refer to the Equipment List in Section 6 of this Handbook 910 7 SYSTEM DESCRIPTION 910 7 1 CONTROLS AND INDICATORS nat AA83 dent Dual Control NM ICS Volume inner LIVE gt MAX Pilot VOX outer ICS PILOT voL gt Ho y ED s Annunciator 2 D e MODE Switch Ven MUSIC COPLT vo le Dual Control Music Volume inner Copilot VOX outer LK N e LIVE SS MAX 910 4 Page Date 6 April 2010 Pilot s Operating Handbook Section 910 EXTRA 300LT XTRA NAT AA83 001 Intercom ICS VOL PILOT VOX This control is a fluted concentric rubber knob on the top of the panel The inner front knob is the ICS VOL control which is used to set intercom volume It is at minimum volume when fully counterclockwise ccw As the knob is rotated clockwise cw the ICS volume for the crew increases The ICS is muted during transmit operations The outer rear knob is the PILOT VOX control that contro
14. Pilot s Operating Handbook Digital RPM Indicator XTRA EXTRA 300LT Left blank intentionally 906 2 Page Date 6 April 2010 Pilot s Operating Handbook Section 906 EXTRA 300LT XTRA Digital RPM Indicator 906 906 1 906 2 906 3 906 4 906 5 906 6 906 7 DIGITAL RPMINDICATOR GENERAL The EXTRA 300LT is as standard equipped with the P 1000 Digital rpm indicator LIMITATIONS Not affected EMERGENCY PROCEDURES Not affected NORMAL PROCEDURES Not affected PERFORMANCE Not affected WEIGHT AND BALANCE Refer to the Equipment List in Section 6 of this Handbook DESCRIPTION AND OPERATION OF THE SYSTEM The operation of the indicator is straight forward After power is supplied to the indicator the engine is started and the self tests are 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 RPMRANGES The face ofthe indicator is placarded with the unchanged engine rpm operating range Additionally the engine operating ranges are indicated by the large gr
15. T 0008 5 a 2 0009 gt i d 2 000 I 0006 00001 amod Sy Je uiu Gp jo eese WD e 10 ED SN 2 8 194 gg seat DEI pue dn wiem JOY Ee SN Je G sse IED sn z 99 a eoz any eo MT 00011 sql renz 6x 066 Be suonipuoo 00021 06 OLE OSE oee ole 066 046 OSC OES SVL y u paads esini Page Date 6 April 2010 5 14 Pilot s Operating Handbook Section 5 EXTRA 300LT XTRA Performance 5 11 CRUISEPERFORMANCE Range and Endurance values for a T O Weight of 950 kg 2095 Ib including fuel for warm up and Take Off from SL max cont Power climb to cruising altitude and a reserve of 21 L 5 55 US gal for 45 minutes with 45 Power 5 5 L 1 45 US gal unusable fuel is taken into account At ISA Conditions PA Eng Manif Power Setting Fuel TAS IAS Endur Range Mixture Press Consumption 1 2 ft m rom inHg 96 hp L h gal h kts km h kts km h h nm km Best SL 2700 29 3 100 315 99 5 263 202 374 203 376 1 72 347 642 Power 0 2600 29 3 90 284 85 2 22 5 193 357 194 360 2 01 387 717 Power 2400 25 4 75 236 69 9 18 5 177 328 179 332 2 45 434 804 Power 2200 24 6 65 205 51 5 13 6 165 305 167 309 3 32 546 10
16. 21 1 4 8 16 3 NM Associated conditions Descend speed 150 KIAS ca 15 Hg 2500 RPM Fuel US Gal 0 0 0 5 10 1 5 20 2 5 30 3 5 40 4 5 50 55 6 0 65 7 0 7 5 8 0 8 5 9 0 12000 hht HA TT 3600 11000 3200 10000 2800 9000 8000 2400 7000 E 2000 E lt 6000 lt 1600 5000 p 4000 1200 3000 800 2000 Time Distance 400 1000 Fuel 0 Y 0 12 14 16 18 20 22 24 26 28 30 22 Time Fuel Distance Min Liter Nautical Miles 5 16 Page Date 6 April 2010 Pilot s Operating Handbook XTRA Section 5 EXTRA 300LT Performance 5 13 LANDING PERFORMANCE Power Idle Runway Concrete Brakes maximum NOTE For every knot 1 852 km h headwind the landing distance can be decreased by 3 On a solid dry and plain grass runway the landing is increased by 15 Landing distance in meter for landing roll Roll and landing distance over 50 ft obstacle 50 ft Weight 820 kg 1808 Ibs approach speed 90 KIAS 167 km h OAT gt 20 4F 10 C 14 0 C 32 10 C 50 20C 68 30 C 86 F 40 C 104 F PA ft m R
17. 7 1 THE AIRCRAFT The aircraft EXTRA 300LT is designed and developed by EXTRA Flugzeugproduktions und Vertriebs GmbH Flugplatz Dinslaken 46569 H nxe Federal Republic of Germany in accordance with the U S Federal Aviation Regulations part 23 categories normal and acrobatic to fullfill the primary flight training normal operation rules and acrobatic training combined with excellent touring capabilities EXTRA 300LT is alight weight robust single piston engined two seat aircraft with a fuselage structure in tig welded steel tube construction The landing gear wing and tail are made of epoxy reinforced with glass and carbonfiber The items are qualified up to 72 C 161 6 F Not to exceed this temperature limit an appropriate colour specification for composite structure is given by the manufacturer document EA 03205 19 To check the temperature inside the cockpit potential green house effect a reversible temperature indicator STRUCTURAL OVERHEAT INDICATOR is applied on the wing main spar in the carry through section After reaching the temperature limit of 72 C 161 6 F the word RISK appears on the red spot of this structural overheat indicator immediately and flying is prohibited When the structure cools down below this temperature limit the word RISK disappears and you may go on with the preflight checklist a Below 72 C 161 6 F b At 72 C 161 6 F or above STRUCTURAL CAUTION STRUCTURAL CAUTION OVERHE
18. 7 3 WINGS The wing is of CRP construction The dual chamber main spar fullfilling the requirement for fail safe design consists of carbon roving caps combined with CRP webs Core foam is a PVC foam Divinycell HT 50 The wing shell is built by a Honeycomb sandwich with CRP Laminates On the surface there is a protective layer of GRP To prevent buckling of the shell plywood ribs are used In the area of the wingtanks is a layer of CRP laminate with an incorporated aluminium thread bonded to the metal fuselage structure as means of lightning protection The 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 behind the main spar 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 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 300LT possesses a cruziform empennage with stabilizers and moveable control surfaces The rudder is balanced aerodynamically atthe tip Spars consist of PVC foam cores CRP caps and GRP laminates The shell is built using honeycomb sandwich with GRP laminate
19. 917 5 PERFORMANCE Notaffected 917 6 WEIGHT amp CENTER OF GRAVITY Refer to the Equipment List in Section 6 of this Handbook 917 7 SYSTEMDESCRIPTION 917 7 1 GENERAL Refertothe Aspen Pilot s Guide s as specified in paragraph 917 1 fordescription ofthe EFD1000 500 System 917 7 2 PITOTOBSTRUCTION MONITOR CONFIGURATION 5 ONLY The Pitot Obstruction Monitor is available only in configuration 5 EFD1000 PFD Pro and EFD1000 MFD A common pitot and static input is shared between the EFD1000 PFD the EFD1000 MFD and the primary airspeed indicator Should one or both of these lines become blocked such as might occur due to an inadvertent icing encounter or from water trapped in the lines then both the EFD1000 PFD and the EFD1000 MFD along with the primary indicators of airspeed and altitude could display erroneous airspeed and altitude information Furthermore because the EFD1000 uses pitot and static pressures as part of the ADAHRS attitude solution loss or corruption of the pitot or static pressures could also influence the accuracy of attitude information The EFD1000 has been shown to be robust to these failures either by being tolerant to incorrect pitot or static inputs or by detecting and annunciating adegraded attitude solution In combination with the installed GPS the system evaluates indicated airspeed and GPS groundspeed to identify conditions indicative of a blockage in the pitot system If a blockage is detected the monitor
20. Left blank intentionally 913 2 Page Date 6 April 2010 Pilot s Operating Handbook Section 913 EXTRA 300LT XTRA GARMIN GTX 327 Transponder 913 1 GENERAL The GARMIN GTX 327 is a panel mounted TSO dtransponder with the addition of timing functions The transponder is a radio transmitter and receiver that operates on radar frequencies receiving ground radar interrogations at 1030 MHz and transmitting a coded response of pulses to ground based radar on a frequency of 1090 MHz M FONG FLIGHT TIME 81 23 20 mmm ESTOP lt NOTE 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 YN CAUTION The GTX 327 should be turned off before starting or shutting down aircraft engine The GTX 327 Transponderis powered on by pressingthe STBY ALT or ON keys or by the AVIONIC switch After power on a start up page will be displayed while the unit performs a self test 913 1 1 MODESELECTIONKEYS OFF Powers offthe GTX 327 STBY Powers on the transponder in standby mode At power on the
21. Longitudinal Flight Control System iii eese e 7 5 Lateral Flight Control System sse nnne nnne nens 7 b Directional Flight Control System 2 1 Iii va dE Ecce ORE RR ee 7 5 Secondary Control ERE 7 5 INSTRUMENTATION seisoene l na ees Ge ee esse in er oio eed Oe ee eg Ee Bee ede ee eds 7 5 Instrument Panel Rear Cockpit iese ee AR AA ee Ge AA AA rca cra 7 6 Instrument Panel Front Cockpit 7 8 We el d i EE EEN 7 8 SEATS SEAT BELTS ELE 7 8 CANOPY EE EE E 7 8 POWER PLAN T 7 9 elc TET 7 9 SIBI AK ER OE EE 7 9 Engine Install RR N OE A 7 10 ee TE 7 10 Rufo RR OE EE RE TE EE e 7 10 VD EE RE ORE E EO ME AN 7 10 lala ise A A R 7 10 Fuel Selector Valve AR RR EE EE EE ia 7 10 Exhaust System ts di tate chad Fee E eed ad ES shen be eo Ae 7 10 FUEL SYSTEM ee 7 10 ELECTRICAL SYSTEM 0 a 7 12 CABIN ENVIRONMENT CONTROL 122212 eeue ees iau conie tauro it kann E en keen EENS NEEN 7 12 BAGGAGE COMPARTMENT ee esse ee ae EE ER AAR REGEER KEER REG sinn nnn asini nnns siia KERE Re nass anna 7 14 LANDING EIGEL ee ee 7 14 Page Date 6 April 2010 7 1 Section 7 Pilot s Operating Handbook Description and Operation of Aircraft and Systems X TRA EXTRA 300LT Left blank intentionally 7 2 Page Date 6 April 2010 Pilot s Operating Handbook Section 7 EXTRAS300LT X TRA Description and Operation of Aircraft and Systems SECTION7 DESCPRIPTION AND OPERATION OF AIRCRAFT AND SYSTEMS
22. Maneuvers Airspeeds minKIAS maxKIAS Segment Horizontal Line 45 climbing 90 up 45 diving 90 diving 1 4 Loop climb Loop Stall turn Maneuvers Airspeeds min KIAS max ALE Aileron roll Snap roll Tail slide Spin Inverted spin Inverted flight Less than 4 min Knife edge Less than 10s Approved acrobatic maneuvers and recommended entry airspeeds Maneuvers Airspeeds min km h max km h Segment Horizontal Line 45 climbing 90 up 45 diving 90 diving 1 4 Loop climb Loop Stall turn in both cockpits Maneuvers Airspeeds min km h max km h Aileron roll Snap roll Tail slide Spin Inverted spin Inverted flight Less than 4 min Knife edge Less than 10 s Page Date 6 April 2010 Section 2 Pilot s Operating Handbook Limitations XTRA EXTRA 300LT 2 14 3 INSTRUMENT MARKINGS AIRSPEED INDICATOR greenarc 65 KIAS 120 km h 160 KIAS 296 km h yellow arc 160 KIAS 296 km h 221 KIAS 409 km h redline 221 KIAS 409 km h OIL PRESSURE INDICATOR red line 25 psig yellow arc 25 psig 55 psig greenarc 55 psig 95 psig yellow arc 95 psig 115 psig red line 115 psig OILTEMPERATURE INDIGATOR yellow arc lt 140 F greenarc 140F 210 F yellow arc 210 245 red line 245 F CYLINDERHEAD TEMPERATURE INDICATOR yellow arc lt 150 F greenarc 150 F 435 F yellow arc 435 F 465 redline 465 F RPMINDICATOR greenarc 700 rpm 2700 rpm re
23. NOTE Since the maximum horizontal speed is 205 KIAS 380 km h higher speeds should be avoided in acrobatics since an unnecessary loss of altitude would occur Torquemaneuvers All maneuvers with high angular velocity associated with high propeller RPM must be considered dangerousforthe engine crankshaft Although wooden composite propeller blades are used the gyroscopic forces at the prop flange are extremely high YN 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 6 April 2010 4 11 Section 4 Pilot s Operating Handbook Normal Procedures gt XTRA EXTRA 300LT 4 12 3 SPIN To enter a spin proceed as follows Reduce speed power idle When the plane stalls Kick rudder to desired spin direction Hold ailerons neutral Stick back positive spinning Stick forward negative spinning The plane will immediately enter a stable spin Ailerons against spin direction will make the spin flatter Ailerons into spin direction will lead to a spiral dive Above apply for positive and negative spinning To stop the spin Apply opposite rudder Make sure power idle Holdailerons neutral Stick to neutral position The plane will recover within 1 2 turn Recovery can still be improved by feeding in in spin ailerons NOTE If ever disorientation should occur during spins
24. Pilot s Operating Handbook XTRA Emergency BO EXTRA 300LT 3 2 4 OILSYSTEM MALFUNCTION If oil pressure indicates low Apply positive g If oil pressure is not regained then 1 Airspeed 85 KIAS 157 km h 2 Throttle REDUCE TO IDLE 3 Engine oil temperature OBSERVE INDICATION 4 Land ASAP V WARNING If oil pressure drops to 0 psi kPa the propeller pitch changes automatically to coarse high pitch with a corresponding decrease in RPM 3 2 5 ALTERNATORFAILURE An alternator failure is indicated by the red light of the low voltage monitor If red light illuminates 1 Digital voltage indication CROSS CHECK If indication is above 13 V alternator is in function 2 Flight CONTINUE if it is not 3 rpm CHECK min 2500 rpm 4 Alternator switch OFF AND ON 5 ALT FIELD Circuit breaker PULL AND RESET 6 Lowvoltage monitor CHECKINDICATION If red light is off 7 Flight CONTINUE If red light illuminates again 8 Land AS SOON AS PRACTICAL 3 3 FORCED LANDINGS 3 3 1 EMERGENCY LANDING WITHOUT ENGINE POWER 1 Seat belts shoulder harnesses SECURE 2 Airspeed 85 KIAS 157 km h 3 Mixture IDLE CUT OFF 4 Fuel shutoff valve OFF Pull amp Turn 5 Ignition switch OFF 6 Battery switch OFF 7 Alternator switch OFF 8 Touchdown SLIGHTLY TAILLOW 9 Brakes OPTIMUM BRAKING Page Date 6 April 2010 Section 3 Pilot s Operating Handbook Emergency Procedures XTRA EXTRA 300LT 3 3 2 PRECAUTIONARY LANDING WITH ENGI
25. or Century Kollsman or Pioneer or Bendix or Jaeger 34 AN5745 32989 32990 33427 33079 33588 FI3001 0 30 0 30 0 96 0 50 0 17 0 40 1 35 1 35 1 41 0 57 0 60 1 60 Lights 33 Ed gt YP s __ __ 2222 _ _ _ __ A __ ___ A _ EE EE EE EE AE EE gt o mx d J or Century AN5745 01206 0 30 1 60 A 1 Magnetic Compass SIRS Navigation Ltd 33085 0 13 1 62 R 1 Magnetic Compass Airpath 00189 0 25 1 62 A 1 Airspeed Ind front United Instr UI8030 B 891 33424 0 32 0 65 O 1 Airspeed Ind front United Instr UI8030 B 900 33875 0 32 0 65 A dual scale 1 Airspeed Ind front kts Mikrotechna Praha LUN 1106 K2B4 LT 34157 0 50 0 65 A 1 Airspeed Ind front km h Mikrotechna Praha LUN1106 P2B4 LT 34158 0 50 0 65 A 1 Airspeed Ind rear United Instr UI8030 B 891 33424 0 32 1 61 R Page Date 18 June 2013 6 11 Section 6 XTRA Pilot s Operating Handbook Weight and Balance and Equipment List EXTRA 300LT QTY ITEM MANUFACTURER MODEL NO PART NO WEIGHT ARM INST R kg m O A 1 Airspeed Ind rear United Instr UI8030 B 900 33875 0 32 1 61 A dual scale 1 Airspeed Ind rear kts Mikrotechna Praha LUN 1106 K2B4 LT 34157 0 50 1 61 A 1 Airspeed Ind rear km h Mikrotechna Praha _ LUN 1106 P2B4 LT 34158 0 50 1 61 A 1 Alternate Static Valve Extra 300 L Option
26. to the end FIND Weight C G 6 3 2 Weight and Balance Record Sheet EMPTY WEIGHT PILOT COPILOT ACRO FUEL WING FUEL Y W G E WxX EW 2086 1 lbs 32 8 inch WEIGHT MOMENT E WxX Page Date 6 April 2010 Section 6 Pilot s Operating Handbook Weight and Balance and Equipment List XTRA EXTRA 300LT 6 4 LOADING WEIGHTS AND MOMENTS PILOT amp PILOT REAR SEAT COPILOT FRONT SEAT PARACHUTE Arm 207cm 81 5 inch Arm 2 98 cm 38 4 inch WEIGHT MOMENT MOMENT Ibs kg x cm in x Ibs kg x cm in x Ibs 10758 5068 11654 5491 12551 5913 13447 6336 14344 6758 15240 7180 16137 7603 17034 8026 17930 8448 BAGGAGE BAGGAGE COMPARTMENT Arm 331cm 130 3 inch WEIGHT MOMENT kg Ibs kg x cm in x Ibs 5 11 1655 1434 10 22 3310 2867 FUEL ACRO amp CENTER TANK FUEL WING TANK Arm 28 30 cm 11 12 inch Arm 83 cm 32 7 inch CONTENTS WEIGHT MOMENT CONTENTS WEIGHT MOMENT Liter kg x cm Liter kg kg x cm US Gal lbs x in US Gal Ibs in x lbs 65 143 10 26 72 159 598 519 A 81 8 20 53 144 31 8 1195 1037 18 0 39 7 40 10 6 288 63 5 2390 2075 216 476 60 15 9 43 2 953 3586 3112 25 2 55 6 80 21 1 57 6 127 0 4781 4150 28 8 63 5 100 26 4 72 0 158 8 5976 5187 324 71 4 120 31 7 86 4 190 5 7171 6224 36 0 79 4 140 37 0 100 8 222
27. 1 6 915 1 7 915 2 915 3 915 3 1 915 4 915 5 SECTION 915 GARMIN GTX 330 TRANSPONDER Table of Contents Page GENERAL coria de 915 3 Mode Selection Keys AA 915 4 Gode SeleCHOR EE 915 4 Keys for other GTX 330 Functions 122121 dd ee ee ee ee AR RA ee ee Ge eene 915 5 Function DiS DIA se sr ms 915 5 Configuration Oe e EE 915 6 Altitude tee Mine et e 915 6 Failure Annunciation ee AR ee AA Re AA AA AA nennen nennen essen ee Ee Re AA de de de ee 915 6 IMITATIONS OE N EE EEN 915 7 EMERGENCY PROCEDURES 3 25 62 we ed Gees ee Ne ee Ee ae De ee ee rss ee ee eed ei 915 7 IMPORTANT CODES RE N OE OE 915 7 NORMAL PROCEDURES ee 1 oase Se eens ee annie Cx d t l aee ioc ui due es ads 915 7 PERFORMANCE 915 7 Page Date 6 April 2010 915 1 Section 915 Pilot s Operating Handbook GARMIN GTX 330 Transponder XTRA EXTRA 300LT Left blank intentionally 915 2 Page Date 6 April 2010 Pilot s Operating Handbook Section 915 EXTRA 300LT XTRA GARMIN GTX 330 Transponder 915 1 GENERAL The Garmin GTX 330 panel mounted Mode S Transponderis aradio transmitter and receiverthat 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 se
28. 133 90 Panel MN IDENT 117 95 1200 STRY Ti EU KT YA intercom Mon Sg or Audio Panel Monitored Radios MIC Selection s COM 1 COM 1 plit Split Mode Mode COM 2 COM 2 Playback Monitor and Contrals Control Passenger Mic Selections Address NL EET Not used Speaker V alim Marker Marker Not used Audia Volume Marker Not used Hi Sense TT END DEMO t Com Freq Psh Nav P Figure 5 GTN 750 Audio Panel Operation Page Date 6 November 2012 922 13 Section 922 Pilot s Operating Handbook GARMIN GTN 635 650 750 XTRA EXTRA 300LT PLAYBACK CONTROLS 1 While the Audio Control page is displayed touch the Playback Controls key to display the Playback Controls selections 2 Touch the Playback Volume arrows to set volume 3 Touch the Backward Play or Forward keys to control the playback of the currently selected recording 4 Touch the Previous or Next keys to select a recording INTERCOMSETUP 1 Touch the Intercom window at the top of the display to display the intercom Setup page 2 Touch the arrow between the Pilot and CO Pilotto activate communication between those recipients The arrow will be green when communication is active Touch the arrow again to deactivate communication 3 Touch the Pilot or Co Pilot keys to set the Volume and Squelch for the selected item 4 Touch the Volume arrows to set the desired Volume level 5 Touch the Auto Squelch key to allow the
29. 1956 2262 2617 508 562 624 693 801 927 1557 1724 1912 2123 2456 2841 550 609 675 750 867 1003 1685 1866 2069 2298 2658 3074 593 657 729 809 936 1083 1819 2014 2233 2480 2869 3318 639 707 784 871 1008 1165 1958 2168 2404 2670 3088 3572 686 760 842 936 1082 1252 2103 2329 2582 2868 3317 3837 Weight 870 kg 1918 Ibs approach speed 81 KIAS 150 km h OAT 2 PA ft m 20 C 4F Roll 50ft 10 C 14 F Roll 50 ft 0 C 32 F Roll 50 ft 10 C 50 Roll 50ft 20 C 68F Roll 50ft 30 C 86F Roll 50ft 40 C 104 F Roll 50 ft SL 2000 610 4000 1219 6000 1829 8000 2438 10000 3048 467 517 573 637 736 852 1431 1585 1757 1951 2257 2611 508 563 624 693 802 927 1558 1726 1913 2125 2458 2843 552 611 678 752 870 1007 1692 1873 2077 2307 2668 3086 597 661 733 814 942 1090 1831 2027 2248 2496 2887 3340 645 714 792 879 1017 1176 1976 2188 2426 2694 3117 3605 694 769 852 946 1095 1266 2128 2356 2612 2901 3355 3881 745 825 915 1016 1176 1360 2285 2530 2806 3116 3604 4168 Weight 950 kg 2095 Ibs approach speed 85 KIAS 157 km h OAT gt PA ft m 20 C 4F Roll 50ft 10 C 14 Roll 50 ft 0 C
30. 2 8366 7262 39 6 87 3 432 95 2 46 8 103 2 6 8 Page Date 6 April 2010 Pilot s Operating Handbook Section 6 EXTRA 300LT der XTRA Weight and Balance and Equipment List 6 5 WEIGHTS AND MOMENTS LIMITS Weight 73 0 cm 75 0 cm 80 0 cm 84 1 cm MTOW kg Ibs 28 7 29 5 31 5 33 1 NORMAL A 950 2095 Ska 900 1985 an S ET 820 1808 NA 800 1764 ON 1764 NQ S 750 1654 1 N 700 1544 E NS H gt NS 777 TT 650 1433 E S 0 0 YM SS i T pae UU 07 75 0 80 0 850 880 Amien 27 8 29 5 31 5 33 5 34 6 Arm inch Example At 850 kg 1874 lbs and 68000 kgcm 59031 in lbs the C G location is 80 0 cm 31 5 aft of ref datum Page Date 6 April 2010 6 9 Section 6 XTRA Pilot s Operating Handbook Weight and Balance and Equipment List EXTRA 300LT 6 6 EQUIPMENT LIST EXTRA 300LT S N QTY ITEM MANUFACTURER MODEL NO PART NO WEIGHT ARM INST R kg m ra 2 4 4 4 4 4 Wing Tie Down Rings Canopy Lock Venting and Heating 21 Heater Battery Avionic Master CB 40A Alternator 65 Amps Alternator 55 Amps Alternator 65 Amps Alternator 60 Amps Shunt 50A 50mV Volt Ammeter External Power Socket Piper Type Batt Charger Plug 12 V 12VDC Power Outlet Socket Cockpit 25 Safety Belt Assy Rea
31. 26 25 ft 10 84 m 116 68 ft Root NACA23015 mod Tip NACA2301 2 mod Root 1 88 m 6 17 ft Tip 0 843 m 2 77 ft 1 427 m 4 682 ft 2x 0 757 m 2 x 8 15 ft up 30 down 20 tolerance 2 3 20 m 10 50 ft 2 55 m 27 45 ft Wortmann FX71 L 150 30 0 722 m 7 77 ft up 25 toler 2 down 25 toler 2 up 35 down 27 tolerance 2 1 38 m 14 85 ft Wortmann FX71 L 150 30 0 52 m 5 60 ft left right 30 tolerance 2 Page Date 6 April 2010 Pilot s Operating Handbook Section 1 X TRA General EXTRA 300LT 1 4 1 5 1 5 1 1 6 1 7 ENGINE Manufacturer Textron Lycoming Williamsport Plant PA 17701 USA Type Lycoming AEIO 580 B1A Ratedpower 315 HP 235 kW 2700 RPM 303 HP 226 kW 2600 RPM 286 HP 213 kW O 2400 RPM PROPELLER Manufacturer MT Propeller Entwicklung GmbH Federal Republic of Germany Type MTV 9 B C C 198 25 3 blade constant speed EXHAUST SYSTEM Manufacturer Gomolzig Flugzeug und Maschinenbau GimbH Federal Republic of Germany Complete 6 in 1 System with integrated Silencer FUEL Fuel type AVGAS 100 100 LL for alternate fuel grades see later issues of Textron Lycoming S I No 1070 Minimum 100 130 octane Maximum 115 145 octane Total fuel capacity 221L 58 4US gal Wingtanks 2 x 76 L 152L 40 2US gal Center tank 60L 15 9US gal Acro tank 9L 2 3 US gal Usable fuel capacity in the system 209L 5
32. 422 493 578 706 865 626 729 851 997 1218 1492 406 473 552 647 791 969 700 816 953 1117 1365 1672 452 527 616 722 883 1082 780 909 1062 1245 1523 1867 502 585 684 802 981 1203 866 1009 1180 1384 1693 2076 555 647 757 888 1087 1334 958 1117 1306 1532 1876 2301 612 714 835 980 1201 1474 1056 1232 1441 1691 2072 2543 673 785 919 1079 1322 1624 1160 1354 1585 1861 2281 2801 Weight 950 kg 2095 Ibs Rotating speed 70 KIAS 130 km h OAT gt 20 C 4F PA ft m Roll 50 ft 10 C 14 Roll 50 ft 0 C 82 Roll 50 ft 10 C 50 F Roll 50 ft 20 C 68F Roll 50 ft 30 C 86F Roll 50 ft 40 C 104 F Roll 50 ft SL 2000 610 4000 1219 6000 1829 8000 2438 10000 3048 410 478 558 654 799 978 708 824 963 1128 1378 1687 459 535 625 732 895 1096 792 922 1078 1263 1544 1891 511 596 696 816 999 1224 882 1028 1202 1409 1723 2111 568 662 774 907 1110 1361 979 1141 1335 1565 1915 2348 628 732 856 1005 1230 1509 1083 1263 1477 1733 2122 2603 692 807 945 1109 1358 1667 1194 1393 1630 1913 2343 2876 761 888 1039 1220 1495 1837 1313 1532 1793 2105 2580 3169 Page Date
33. 6 April 2010 EXTRA 300LT Pilot s Operating Handbook XTRA RATE OF CLIMB PERFORMANCE Section 5 Performance 5 6 sql EG9L 6041 b9LL 6181 vaal 6261 b86L 6coc veoc Bx 3uBieM OSL ooz 97 aunyesodwiey sly apis no OOP 0t Ov 0091 0081 0002 00cc uw eyes qua 00pz 009c 0082 PS 000 ooze UWA vOLG op qui lt sql 7861 54 006 3uf amp ieM D emejeduie Jie apisino Y 0009 epnihje eJnsseJg Sjduiex3 Jamod 1seq 1 10008 e oqe uou 30008 Mojeq BINPAN dd 0022 Suonnio es Jamod snonuluoo Xe JeMod SUOMPUOD Page Date 6 April 2010 5 10 Section 5 Performance Pilots Operating Handbook EXTRA 300LT XTRA TIME DISTANCE FUEL TO CLIMB 5 7 cl INN HI uiu e uejsiq en4 eu LL OL 6 8 L 9 G b Z L 0 A X WN ZS 6L L LU quiro 0 eouejsiq 0001 1911 96 S Z9 9 Z Ou 0j lend uiu G Z 0 zeg quio oj eui L a 000Z IV SSeJd 14 0008 eem IV SseJd 14 0002 eynuedeq 000 ejduex3 l 000 l l 0008 I 9 Ed
34. An annunciator will indicate that TWS is inhibited TWS can be inhibited for all applications except Synthetic Vision by selecting SV ONLY When TWS is inhibited no terrain warning is provided Terrain obstacle caution and warning messages are generated due to nearby terrain or obstacles On anon precision approach a terrain caution or warning is probable depending on the rate of descent toward the terrain Landings at most airports do not generate an alert Some airports with unusual topography may generate alerts when the flight path marker points toward nearby higher terrain 917 7 9 ASPEN PFD AS ENCODED ALTITUDE SOURCE The EFD1000 PFD can provide encoded altitude information to connected units Do not unpower the Aspen PFD when using the Garmin GTN 635 650 750 or the GTX 33 remote transponder 917 8 HANDLING SERVICING AND MAINTENANCE If the temperature sensor of the RSM is suspected to fail it is advisable to initiate a check of the RSM vent hole Consider that it is necessary to remove the aircraft tail fairing for that purpose Replace the EFD internal battery every 3 years or 2200 hours Check unit and wiring every 100 hours or during annual inspection Refer to Aspen Document 900 0001 2 001 latest revision for Instructions for Continued Airworthi ness 917 12 Page Date 6 November 2012 uere EXTRA SECTION 918 EI MVP 50P Table of Contents Paragraph Page 918 1 GENERAL ooo aiii 918 3 918 2 LIMITATION
35. E fault indications 911 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 911 2 LIMITATIONS Not applicable 911 3 EMERGENCY PROCEDURES 911 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 911 4 NORMAL PROCEDURES Notapplicable 911 5 PERFORMANCE Not applicable 911 8 Page Date 6 April 2010 Pilot s Operating Handbook X TRA EXTRA 300LT Paragraph 912 1 912 1 1 912 1 2 912 1 3 912 1 4 912 1 5 912 1 6 912 1 7 912 1 8 912 1 9 912 1 10 912 2 912 3 912 3 1 912 4 912 5 SECTION 912 BECKER ATC 6401 TRANSPONDER Table of Contents Page ic 2 gU M deg 912 3 Controls and Indicators sioi oreen aieiaa Re AA ee nennen enne a atan nnns nens 912 4 Switching on the Unit pre flight check sse 912 4 Nei CIR UTER 912 5 Squawk Selection Ju oio eet it EE RE ue 912 5 e El E Hm 912 6 Selftests of the Unit BL IS ente ted o nee ene t aee ee Ee ner d sex Er lactea 912 6 Selection urs E MOERS 912 7 Flight Operation in Mode A C S reply code and altitude code 91
36. EXTRA 300LT XTRA Section 5 Performance Take off distance in feet for take off roll Roll and take off distance over 50 ft obstacle 50 ft Weight 820 kg 1808 Ibs Rotating speed 65 KIAS 120 km h OAT gt 20 C 4F PA ft m Roll 50 ft 10 C 14 Roll 50 ft 0 C 82 Roll 50 ft 10 C 50 Roll 50 ft 20 C 68 F Roll 50 ft 30 C 86 F Roll 50 ft 40 C 104 F Roll 50 ft SL 2000 610 4000 1219 6000 1829 8000 2438 10000 3048 334 389 454 532 650 796 576 671 784 918 1122 1373 373 435 508 596 728 892 644 751 877 1028 1257 1539 416 485 567 664 813 996 718 837 978 1146 1402 1718 462 538 630 738 903 1108 797 929 1086 1274 1559 1911 511 596 697 818 1001 1228 881 1028 1202 1411 1727 2118 563 657 769 902 1105 1357 972 1134 1326 1557 1907 2341 619 723 846 993 1217 1495 1068 1247 1459 1713 2100 2579 Weight 870 kg 1918 Ibs Rotating speed 67 KIAS 124 km h OAT gt 20 C 4F PA ft m Roll 50 ft 10 C 14 Roll 50 ft 0 C 82 Roll 50 ft 10 C 50 F Roll 50 ft 20 C 68F Roll 50 ft 30 C 86F Roll 50 ft 40 C 104 Roll 50 ft SL 2000 610 4000 1219 6000 1829 8000 2438 10000 3048 363
37. Engine Shock Mount Fuel Oil 8 Sense Lines in Eng Comp Set Engine Fuel System 73 Fuel Injector Mech Fuel Pump Ignition 74 Ignition Switch Magneto LH Magneto RH Slick Start Magneto Start Booster Lycoming Barry Parker Stratoflex Precision Avstar Crane Lear Romec Hartzell Engine Tech TCM Slick Slick Unison AEIO 580 B1A R H ENPL RT10427 RSA 10 AD 1 RG9080 J4A PN 200F 5002 6393 6350 SS1001 32712 01817 33315 61M26404 62E22581 62E23186 00185 32860 02337 32598 191 72 0 72 R 1 70 0 29 R 3 70 0 15 R 3 90 0 68 0 57 0 30 R 0 57 0 30 A 0 15 1 63 2 30 0 15 2 00 0 15 0 27 0 02 R Page Date 22 April 2015 Pilot s Operating Handbook Section 6 EXTRA 300LT eed XTRA Weight and Balance and Equipment List QTY ITEM MANUFACTURER MODELNO PART NO WEIGHT ARM INST R kg m o A Engine Controls 76 1 RPM Vernier Control ACS Products Co 00113 0 71 0 82 R 1 Mixture Vernier Control ACS Products Co 00112 0 65 0 94 R 1 Throttle Control Teleflex Marine 33052 0 56 0 60 R 1 Throttle Control Cable Cablecraft 580 540 501 33589 0 63 0 60 A Engine Indicating 77 Conventional engine gauges 1 RPM Indicator digital Horizon P100 230 643 00 02489 0 68 1 60 R 1 Oil Press Oil Temp Ind D2 OP130U 2 1 4 UMA OT300U 01 33428 0 09 1 62 R 1 Oil Temp Probe
38. FLIGHT OPERATIONIN 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 ofthe aircraftto ATC A R onthe left nextto the Code on the display signals thetransponder 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 6 April 2010 912 9 Section 912 2 Pilot s Operating Handbook BECKER BXP 6401 Transponder XTRA EXTRA 300LT 912 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 912 1 10 CONFIGURATION MODE The configuration mode is available
39. GRAVITY CALCULATION SAMPLE PROBLEM SHEET 2 Weight and Balance and Equipment List Section 6 youuu S SL CH 9 22 9 82 VuM 069 009 EH 0 02 069 00 I i I I I I I I T V 0 0 5 i T d Fees pa base 4 p TS geh 069 l Ajdwa xuejBuiw um juo iuBiew Adug 8 SJaAnauew oneqoloy J E vryer 004 5 ALON L eo o I S AE 3 T ron OSL T R aa a T 3 p92 008 s Em 8081 028 S 1VO OLUVSOMOV MOLN F 3 181 068 8161 0 8 II 1VO DILWIOSIV MOLN T ms E 861 006 8102 S16 B aa a T c602 066 res Luet IW 1V9 OUVSOMOV 8 TVINHON MOLN T OVINYE 0 WO pg OVINYS zz WO 0 EZ y slo EA Page Date 6 April 2010 Pilot s Operating Handbook EXTRA 300LT XTRA Section 6 Weight and Balance and Equipment List 6 3 1 Sample Take off Condition Aircraft Empty Weight Pilot On Rear Seat Copilot On Front Seat Baggage Center amp Acro Tank Fuel 67 690 0 kg 1521 2Ibs 99 0 kg 218 3 Ibs 99 0 kg 218 3 lbs 10 0 kg 22 0 Ibs 48 2 kg 106 3 Ibs 946 2 kg 2086 1 Ibs To find C G follow line Pilot 99 kg from Empty Weight to the end Continue on line Copilot 99 kg Now follow line Baggage 10 kg and then the line Fuel C amp A Tank 67
40. T O distance can be decreased by 496 For every 3 kts 6 km h tailwind up to 10 kts 19 km h the T O distance is increased by 1096 On a solid dry and plain grass runway the T O is increased by 1596 Take off distance in meter for take off roll Roll and take off distance over 50 ft obstacle 50 ft Weight 820 kg 1808 Ibs Rotating speed 65 KIAS 120 km h OAT gt 20 C 4F 10 C 14 0 C 32 10 C 50 20 C 68 30 C 86 F 40 C 104 F PA ft m Roll 50ft Roll 50ft Roll 50ft Roll 50ft Roll 50ft Roll 50ft Roll 50ft SL 102 176 114 196 127 219 141 243 156 269 172 296 189 326 2000 610 119 204 133 229 148 255 164 283 182 313 200 346 220 380 4000 1219 138 239 155 267 173 298 192 331 212 366 234 404 258 445 6000 1829 162 280 182 313 203 349 225 388 249 430 275 475 303 522 8000 2438 198 342 222 383 248 427 275 475 305 526 337 581 371 640 10000 3048 243 418 272 469 304 524 338 583 374 646 414 713 456 786 Weight 870 kg 1918 Ibs Rotating speed 67 KIAS 124 km h OAT gt 20 4F 10 C 14 0 C 32 F 10 C 50 20 C 68 30 C 86 40 C 104 F PA ft m Roll 50
41. UMA 1B3A 33428 0 08 0 11 R 1 Oil Press Sender UMA N1EU150G A or 33428 0 12 0 04 R T1EU150G A 1 Manifold Pressure Fuel Flow Ind United Instr UI6331 H 217 33448 0 49 1 60 1 Fuel Cont Ind Wing Datcon 33412 0 14 1 62 1 Fuel Cont Ind Fuselage Tank Datcon 33443 0 14 1 62 R Optional add on to convent eng Gauges 1 EGT CHT Indicator UMA D2 ET1K7K CT600J 01 33438 0 07 1 62 O 1 EGT Probe UMA 2BU20 0 06 0 37 O 1 CHT Probe UMA 2B18 or 2B02 0 05 0 20 O Option Integrated Engine Instrument System 1 Engine Instr Display Electronics Intern MVP 50P EX 01 33108 0 86 1 55 O 1 Engine Data Converter Electronics Intern EDC 33P 33283 1 00 0 42 O 1 Fuel Flow Transducer Electronics Intern FT 60 33288 0 78 0 57 O 6 EGT Probes Electronics Intern P 110 33569 0 26 0 72 O 6 CHTProbes Electronics Intern P 100 33568 0 16 0 72 O 1_ Oil Temp Probe Electronics Intern P 120 33289 0 02 0 09 O 1 OAT Probe Electronics Intern P 128 33290 0 02 0 77 Q 1 Man Press Transducer Electronics Intern PT 30ABS 33284 0 11 0 25 O 1 Oil Pressure Transducer Electronics Intern PT 100GA 33286 0 05 0 05 O 1 Fuel Press Transducer Electronics Intern PT 30GA 33285 0 05 0 05 O 1 Resistive Fuel Level Mod Electronics Intern RFLM 4 12V 33109 0 20 0 31 O Exhaust 78 E A a 1 Exhaust System 6 in 1 Gomolzig EA300 606000 33891 8 48 0 39 R incl Silencer 1 2 inlet
42. a e Ps eee eed ed a pee ba ea s sr ES SS sis BER EJ SIE NIS SIST EO po oc E tE ES NIN TA 2 N if 100 Saf 5001 152 z v E x x v Z E A v E el v z 2 YN o E X v lt E x E E x v Hu O c x Page Date 6 April 2010 Pilot s Operating Handbook XIRA EXTRA 300LT Paragraph 2 1 2 2 2 3 2 4 2 4 1 2 4 2 2 5 2 6 2 7 2 7 1 2 7 2 2 7 3 2 8 2 8 1 2 8 2 2 9 2 9 1 2 9 2 2 10 2 11 2 11 1 2 12 2 13 2 14 2 14 1 2 14 2 2 14 3 2 15 2 16 SECTION 2 LIMITATIONS Table of Contents Page icd zl 2 3 AIR SPEED MAS a Rees 2 3 CROSS WIND COMPONENT ciosiiinaioiiia iaa 2 3 ENGINE m ind 2 3 RR vaeeds nevis 2 3 Engine LIMON se AE RE EO EA OE EK 2 4 PROPELLER iii N EE EE EE ER ON 2 5 WEIGHT LIMITS PR 2 5 WEIGHT AND C G ENVELOPE ies see es eers gee ede anre nca tone eene co Ke ee nnno gek ee das 2 5 Normal Category and Acrobatic Category III 2 Seats sss 2 5 Acrobatic Category II 2 Seats ee ee ee ee ee ee AA cnn cnn nano cana ee nn ee RA ee nennen 2 5 Acrobatic Category 1 Scania 25 ACROBATIC MANEUVERS EE 2 6 Nc AE A Ee ec Ee ei ee diede 2 6 ACTODAUIC FIG ER OE ER EE lc 2 6 LOAD FACTOR E 2 7 Normal FQN unna R ll N 2 7 ACrODAC dle AE RA EE RE teense 2 7 FLIGHAT CREWILIMITS o cia 2 8 KINDS OF OPERATIONAL LIMITS sees eens see n Rae RR Ge ER EER RA AR E
43. and approved supplements is mandatory Foreign operating rules and any references to such rules in the basic manual and approved supplements are not applicable in Brazil The aircraft must be equipped and operated in accordance with Brazilian operating requirements NOTE A Kinds of Operation Equipment List may not necessarily apply in Brazil Page Date 31 May 2012 921 3 Section 921 Pilot s Operating Handbook AIRPLANES REGISTERED IN BRAZIL XTRA EXTRA 300LT 921 2 LIMITATIONS 921 2 1 KINDS OF OPERATIONAL LIMITS Operation is limited to VFR day Use of GPS is prohibited as primary means for navigation Optional GPS is approved as supplemental means for navigation only Wide Area Augmentation System WAAS functionality Since the WAAS is not available in Brazil any kind of Global Navigation Satellite System GNSS approaches is prohibited even though optional GPS System installed e g GARMIN GNC420W may be capable of receiving WAAS 921 2 2 OPERATING PLACARDS The following placard has to be attached to the aircraft replacing the related placard in English language COMBUST VEL adjacent to both wing fuel tank filler caps and AVGAS 100 100LL fuselage center fuel tank filler cap 921 3 EMERGENCY PROCEDURES Not affected 921 4 NORMAL PROCEDURES Not affected 921 5 PERFORMANCE Not affected 921 6 WEIGHT amp CENTER OF GRAVITY Not affected 921 7 SYSTEMDESCRIPTION Not affected
44. 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 tanks 907 7 DESCRIPTION OF THE SYSTEM Onpilot s demand the smoke system produces atrail of smoke by injection of smoke oil straight paraffin oil into the engine exhaust The smoke oil is vaporised by the exhaust gas heat and is visible as dense smoke after leaving the exhaust For smoke system activation the SMOKE ARM switch located on the pilot instrument panel needs to be switched ON first The smoke ON OFF toggle switch is located on top of the Page Date 6 April 2010 907 5 Section 907 Pilot s Operating Handbook Smoke System XTRA EXTRA 300LT throttle lever For filling the smoke oil tanks the SMOKE REFILL switch needs to be ON After the refill process is completed the SMOKE REFILL has to switched OFF When both switches SMOKE ARM and SMOKE REFILL are in the ON position the smoke system is not energized and will not run A pump reversed polarity fills the floptube smoke oil tank through a quick connector located in the aircraft belly fairing This line includes a filter to prevent dirt to enter the smoke system The separate main smoke oil tank is finally filled through the interconnected floptube smoke oil tank Filled tanks are detected by a float switch placed inthe main smoke oil tank which shuts the pump off The same pump
45. are described Limitations are pointed out Segmenthorizontal line A horizontal line may be flown with any speed between Vs and Vye Segment line 45 climbing The plane will follow the line at max power The speed will not decrease below 80 KIAS 148 km h 4 10 Page Date 6 April 2010 Pilot s Operating Handbook Section 4 EXTRA 300LT XTRA Normal Procedures Segment line 90 up Any entry speed may be used Out of a horizontal pull up at 200 KIAS 370 km h the vertical penetration will be 2 500 ft The speed will gradually decrease to 0 NOTE In extremely long lines a RPM decay may occur This is related to a loss of oil pressure Positive g s should be pulled immediately in order to protect the engine Cil pressure will return immediately Segmentline 45 diving Throttle must be reduced in order to avoid exceeding Vye Segmentline 90 diving Throttle must be reduced to idle in order to avoid exceeding Vye Above segments may be filled up with aileron rolls or snap rolls Watch V 160 KIAS 296 km h for aileron rolls with max deflection Snap rolls should not be performed at speeds above 140 KIAS 259 km h Segment 1 4 loop climbing The minimum recommended speed is 100 KIAS 185 km h If the maneuver is to be followed by a vertical line a higher entry speed is required depending on the expected length of the line A complete loop can be performed at speeds above 100 KIAS 185 km h
46. breaker COM circuit breaker Starter circuit breaker Transponder circuit breaker ELT Switch Starter switch 918 8 HANDLING SERVICING AND MAINTENANCE The Level 1 password for maintenance is 00200 The Level 2 Password for system configuration is published on the weighing form of the Aircraft Technical Log 918 6 Page Date 6 April 2010 ctc ln EXTRA SECTION 921 AIRPLANES REGISTERED IN BRAZIL AND OPERATING UNDER THE AGENCIA NACIONAL DE AVIACAO CIVIL REQUIREMENTS Table of Contents Paragraph Page 921 1 GENERA ES Oe Ee 921 3 921 2 M rye c U 921 4 921 2 1 KINDS OF OPERATIONAL LIMITS sess 921 4 921 2 2 OPERATING PLACARDS iese ses eed siene Gees e ne Ged sede eon d uen a de see ene dean aun rca 921 4 921 3 EMERGENCY PROCEDURES 4 ee ee ese ee ees ee ee be ee nennen nnne ee ee AR RE AR ee AA K A Rk ee ee en 921 4 921 4 NORMAL PROCEDURES Eege aa 921 4 921 5 PERFORMANCE iii ER EE NE EE EE OE 921 4 921 6 WEIGHT amp CENTER OF GRAVITY esse ees see ees see ee ee ee Ee Gee ee ee Ee Gee AA ee Ee Gee nnn ee nnne 921 4 921 7 SYSTEM DESCRIPTION niece aii 921 4 921 8 HANDLING SERVICING AND MAINTENANCE esse see ees ees ese ee ee ee ee ee ee ee ee ee ee ee ee 921 5 EASAApproved On Behalf of UH ANAC of Brazil Date 08 Oct 2012 Maximilian Maas uropean Aviation Safety Agency ASP Eno EASA CSV Projec
47. displayed if manual backlighting mode is selected on Configuration Mode Backlighting is controlled by the 8 and 9 keys Page Date 6 April 2010 913 5 Section 913 Pilot s Operating Handbook GARMIN GTX 327Transponder XTRA EXTRA 300LT 913 2 LIMITATIONS Notapplicable 913 3 EMERGENCY PROCEDURES 913 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 913 4 NORMAL PROCEDURES Not applicable 913 5 PERFORMANCE Notapplicable 913 6 Page Date 6 April 2010 Pilot s Operating Handbook X TR A EXTRA 300LT Paragraph 914 1 914 1 1 914 1 2 914 1 3 914 1 4 914 1 5 914 1 6 914 1 7 914 2 914 3 914 3 1 914 4 914 5 SECTION 914 GARMIN GTX 328 TRANSPONDER Table of Contents Page GENERAL cocineta de 914 3 Mode Selection Keys AA 914 4 Code Selecon EE 914 4 Keys for other GTX 328 Functions oooooccconoocccconoccnonancccnnn canon nn ee ee Ge nn nro narran nnne 914 5 Function DISPIAY ms 914 5 Configuration MOde e e erii ctt eee as 914 6 Altitude tee Mine et e 914 6 Failure Annunciation ee RA Re AA Re AA AA ee AA eee ead nne E aaa 914 6 IMITATIONS OE N EE EEN 914 7 EMERGENCY PROCEDURES 3 5 10 00 ee eieaa tute ee ee ee dee 914 7 Imponan CodeS RE N OE
48. enm roca va Reede ENE Ee Ee cpu Ee ege RE 922 8 Touchscreen Key and Knob Functions ee se Re RA ee ee RA ee enne 922 8 Secure Digital Card OR RE ER RE EE a 922 9 Selecting com nav frequencies ii RA AA ee Ge RA RA enne nens 922 9 Remote transponder operation esse ie ee AA Kada ee RKS AE AR RRR KKR AE AK dann 922 10 Remote audio panel operation GTN 750 only ee RA AR ee ee ee 922 12 Powering upthe GIN 635 690 750 genge EE SEE dte GE GESE GE d ni kalla ru GE ER Eu e ge geseg 922 14 Map Page ER Ee Re ia italia 922 15 Ground le eie OE P 922 15 Traffic Display Optional civic pte ertet Es EER SR ee ru tur aser oe Gee ee ee 922 15 SCREEN CLEANING iis Rm 922 15 Page Date 6 November 2012 922 1 Section 922 Pilot s Operating Handbook GARMIN GTN 635 650 750 XTRA EXTRA 300LT Left blank intentionally 922 2 Page Date 6 November 2012 Pilot s Operating Handbook Section 922 EXTRA 300LT XTRA GARMIN GTN 635 650 750 922 1 GENERAL This Airplane Flight Manual Supplement AFMS is written for the Garmin GTN 635 650 750 units The Garmin GTN 635 is a GPS WAAS SBAS capable panel mounted unit that includes an airborne VHF communications transceiver The GTN 650 amp 750 units include all ofthe features of the GTN 635 in addition to airborn VOR localizer LOC and glideslope G S receivers The GTN 750 features a larger display Active Com Nav Standby Com Nav Channel Channel Volume Squelc
49. in minimum blade angle High RPM Warm up at approximately 1000 1200 RPM The engine is ready for take off when the throttle can be opened without the engine faltering 4 6 Page Date 6 April 2010 Pilot s Operating Handbook Section 4 EXTRA 300LT XTRA Normal Procedures 4 5 TAKE OFF PROCEDURE 4 5 1 BEFORETAKE OFF Before you line up at the runway for take off Oil pressure and oil temperature CHECK Magnetos CHECK as follows Engine RPM 1800 min Pay attention to the three small LEDs in the Status area on the upper left corner of the P 1000 face Ignition switch position LEFT Status area Right red LED illuminates Display shows RPM drop Ignition switch position RIGHT Status area Left red LED illuminates Display shows RPM drop Ignition switch position BOTH Status area Right and left red LED remain off 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 must illuminate The maximum allowed RPM drop at 1800 min is 175 min The maximum difference between the magnetos has not to be over 50 RPM identify with the illuminated yellow LED Alternator Output CHECK Propeller control MOVE through its complete range to check operation and return to full HIGH RPM position Boost pump ON check indicator movement on the fuel flow gauge Flight controls CHECK free and c
50. 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 6 April 2010 912 7 Section 912 Pilot s Operating Handbook BECKER BXP 6401 Transponder XTRA EXTRA 300LT SETTING THE FLIGHT NUMBER 1 2 Press SEL button G to enter the select mode Rotate B until Al is displayed Push C to switch to FN The cursor is set on the first character Rotate B to change this character Push C to set the cursor to the next character Repeat steps 4 and 5 until the flight number is entered If the flight number consists of less than 7 characters put a space at the end to fill the remaining characters with spaces Store the changes with STO button F For leaving the setting procedure without storing push the SEL button G NOTE Aircraft Identifier Flight Number consists of max 7 characters on the left hand side oriented No dashes or spaces shall be included If the FN con sists of less than 7 characters the remaining characters on the right side shall be filled with spaces SWITCHING BACK TO DEFAULT Al Press SEL button G to enter the select mode Rotate B to the indication FN XXXXXXXxX First push on C indicates FN Al DEF inverted
51. left corner of the unit Turning it clockwise will turn unit power on and increase the COM radio volume After turning the unit on a welcome page will be displayed while the unit performs a self test followed by the database confirmation pages which show the current database information on the NavData card with the valid operating dates cycle number and databasetype indicated The database is updated every 28 days and must be current for instrument approach operations Information on database subscriptions is available inside your GNC 420W GNS 430W package To acknowledge the database information press ENT 916 7 2 DEFAULTNAVPAGE During mostflights the default NAV map and NAVCOM pages will be the primary pages used for navigation The default NA Vpagedisplays a graphic course deviation indicator CDI the active leg of your flight plan as defined by the current from and to waypoints and six user selectable data fields The default settings for these fields are distance to waypoint DIS desired track DTK bearing to waypoint BRG ground speed GS ground track TRK and estimated time en route ETE The default NA V pageis selected by pressing and holding the CLR key orturning the small right knob Page Date 6 April 2010 916 7 Section 916 Pilot s Operating Handbook GARMIN GNC 420W GNS 430W XTRA EXTRA 300LT Left blank intentionally 916 8 Page Date 6 April 2010 Pilot s Operating Handboo
52. meters dependentupon installation configuration FLIGHT TIME Timer startis configured as either Manual or Automatic When Manual displays the Flight Time controlled bythe START STOP and CLR keys When Automatic the timer begins when take off is sensed Page Date 6 April 2010 914 5 Section 914 F Pilot s Operating Handbook GARMIN GTX 328 Transponder XTRA EXTRA 300LT ALTITUDEMONITOR The ALTITUDE MONITOR function is not available in this installation OAT DALT The OAT DALT function is not available in this installation no temperature input COUNT UP TIMER Controlled by the START STOP and CLR keys Pressing the CLR key zeros the display COUNT DOWN TIMER Controlled by START STOP CLR and CRSR keys The initial Count Down time is entered with the 0 9 keys Pressing the CLR key resets the timer to the initial value STBY The transponder will not reply to any interrogations GND This page is not active CONTRAST This page is only displayed if manual contrast mode is selected during installation configuration Contrast is controlled by the 8 and 9 keys DISPLAY This page is only displayed if manual backlighting mode is selected during installation configuration Backlighting is controlled by the 8 and 9 keys 914 1 5 CONFIGURATION MODE The configurartion mode is not active The GTX328 s options are normally setattime of installation To request any changes ofthe GTX 328 param
53. p 0000 gt ny a 2 Saul vt l 0004 PEL AE 0008 Ha gt 0006 r P Pa gt 00001 V Qum e 0001L 00021 0 GT oz SL ol ie 0 0 e9 sn ena By 056 UBleM INd0042 SVIM 96 peeds Ou SUOMPUOD pajelnossy 11 Page Date 6 April 2010 Pilot s Operating Handbook Section 5 EXTRA 300LT XTRA Performance RANGE 5 8 uu aBuey 069 009 oss 00 0S 00v ose 00 0 4d 0008 INN 96 eBuey lt JeMog 9469 D eJnjejeduie Jie apisino HV said W FZ Y 0008 gen WEIT e ewod y je uiu gy jo masa UD e 10 186 SN 78 000p 186 sal Ky pue dn uuem Joy eb Sn E 7 9 sel eb sn C sa 1607 LE ql v60c puo f T T T T T T T T T 00091 00 ooz OOM 0001 006 008 007 009 00S 00v 00 ooz OO 0 wy ebuey BJ epminiv Ajisueq 5 a1nje1adua ay apisimo OP DE 0c OL 0 OL Oc UC 0t x S s A LAS N VS WS Ys Ys Ss KJ SS S y S S o Q o 7 o o ISA Page Date 6 April 2010 5 12 Section 5 Performance Pilots Operating Handbook EXTRA 300LT XTRA ENDURANCE 5 9 00 s y e
54. place for the G switch to activate the unit The jumperis installed onthe mating half of the connector so that when the connector is installed the beacon is armed This allows the beacon to be handled or shipped without nuisance activation front connector removed NOTE The ELT can still be manually activated using the local switch on the front of the ELT Care should be taken when transporting or shipping the ELT not to move the switch or allow packing material to become lodged such as to toggle the switch 909 7 2 SELF TEST MODE Upon turn off from ON back to ARM state the ELT automatically enters a self test mode that transmits a 406 MHz test coded transmission that monitors certain system functions before returning to the ARM mode The transmission is ignored by any satellite that receives this signal but the ELT requires it to check output power and correct frequency Ifthe ELT is left activated for approximately 50 seconds or more adistress signal is generated that is accepted by the satellites In addition to 121 5 and 406 MHz signalintegrity other operating parameters are checked during the self test Error codes are then generated if other problems are found The error codes are displayed by a series of blinks of the ELT LED remote LED and audio indicator See Installed Transmitter Test section for more details and a description of the error codes NOTE Any time the ELT is activated it is tra
55. pump The boost pump switch is located on the instrument panel A fuel filter with drain is installed between the fuel selector valve and the boost pump Separate drains are located at the lowest point of each tank system Normal float type transducers and electrically operated fuel indicators are used 7 12 ELECTRICAL SYSTEM The electrical system refer to Figure 4 is supplied by a 12 V alternator with integrated rectifier transistor voltage regulator The alternator is mounted on and belt driven by the engine The field current is controlled by the voltage regulator to nominal 14 5 V under all load conditions The ALTERNATOR switch is located on the rear instrument panel Circuit protection against overvoltage is provided by the voltage regulator The alternator installation is rated for a maximum output of 60 amp A 12 V leak proof battery is connected across the alternator output to stabilize the supply and to maintain all essential services in the event of an alternator failure and when the engine is not operating The battery is mounted behind the firewall The BATTERY switch is located on the rear instrument panel All electrical circuits are protected by circuit breakers located on the rear instrument panel and they are easily accessible to the pilot during flight The electrical system features adequate noise suppression to ensure satisfactory operation of the radio equipment All wires switches circuit breakers etc are ma
56. recorded data to a computer LIMITATIONS G V LIMITS Markings and Placards next to the red warning light WARNING LIGHT EMERGENCY PROCEDURES Not affected NORMAL PROCEDURES Not affected PERFORMANCE Not affected Page Date 9 August 2007 904 3 Section 904 F Pilot s Operating Handbook Accelerometer TL 3424 EXT X TRA EXTRA 300LT 904 6 WEIGHT AND BALANCE Refer to the Equipment List in Section 6 of this Handbook 904 7 DESCRIPTION The complete installation consists of OOO o 0000000000000 O QOLUQLU 1 TL 3424 EXT Accelerometer 2 G VLIMITS WARNING LIGHT 3 RS 232c D SUB 9 pins female The TL 3424 EXT is complete weight acceleration management The instrument incorporates a high precision sensor for measuring acceleration in the vertical axis The instrument also incorporates a sensor connected to the Pitot static system for measuring the indicated airspeed Itis possible to download the measured values from the instrument via the serial cable RS 232c into a PC Pressing the Control and Marker Button enters marks into the memory records and enables the user manual control of the memory recording 904 4 Page Date 6 April 2010 Pilot s Operating Handbook X TRA Accelerometer E EXTRA 300LT The TL 3424 EXT checks all measured values at two levels for a warning and an alarm limit signal
57. 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 The CBIT Continuous Built in Test works as follows The continuous BIT acts as a kind of watchdog during operation Negative results of the 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 a power on BIT after switching on Duringthe PBIT any action from other switches are not accepted 912 6 Page Date 6 April 2010 Pilot s Operating Handbook Section 912 EXTRA 300LT XTRA BECKER BXP 6401 Transponder During the PBIT the XPDR is in the SBY mode butthis is notindicated on the display The operating mode indication on the display starts immediately after finalisation of the PBIT Negative results are indicated onthe 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 912 1 7 SELECTIONMODE Press SEL button G and rotate encoder B for selectio
58. the earth s magnetic field to determine aircraft heading pitch and roll The system must be able to periodically sense the earth s magnetic vector to be able to correctly resolve heading and stabilize the ADAHRS attitude solution All magnetic sensors includingthe one inthe EFD1000 will experience degraded performance in the vicinity ofthe earth s magnetic poles When the horizontal component of the earth s magnetic field is no longer strong enough to provide reliable heading data the EFD1000 will detect this condition and compensate for the reduced magnetic fields The system can continue to operate for a short time without reference to magnetic North but must be able to periodically resolve the magnetic vector to continue operations Ifthe EFD1000is unable to resolve the earth s magnetic field for two minutes the system will switch to and annunciate Free Gyro Mode In this mode the ADAHRS continues to provide attitude and heading data based on gyro only operating logic This will be accompanied by a FREE GYRO MODE message posted on the HSI anda CROSS CHECK ATTITUDE annunciation posted on the attitude indicator Under these circumstances increased vigilance and instrument cross check is required If the weak magnetic conditions persist and the EFD1000 is unable to resolve the magnetic vector for six minutes or greater then the attitude and heading solution will be considered failed and will be removed i e Red X d The ADAHR
59. to cover fingers used to operate the GTN unless the Glove Qualification Procedure located in the Pilot s Guide has been successfully completed The Glove Qualification Procedure is specific to a pilot glove GTN unit combination 922 2 7 DEMOMODE Demo mode may not be used in flight under any circumstances 922 3 EMERGENCY ABNORMAL PROCEDURES 922 3 1 EMERGENCY PROCEDURES LOSS OF REMOTE AUDIO PANEL FUNCTIONS IF INSTALLED WITH GTN 750 Pull INTERCOM circuit breaker NOTE This procedure will restore COM operation on the GTN 750 The intercom functions will not be available 922 3 2 ABNORMAL PROCEDURES GPS NAVIGATION INFORMATION NOT AVAILABLE OR INVALID If GTN635 650 750 GPS navigation informationis not available orinvalid the GTN will enter one of two modes Loss of Integrity LOI mode or Dead Reckoning DR mode Utilize remaining operational navigation equipment as appropriate A LOSS OFINTEGRITY MODE If the amber Loss of Integrity LOI Mode message is displayed revert to an alternate means of navigation appropriate to the route and phase offlight or periodically cross checkthe GPS guidance toother approved means of navigation 922 6 Page Date 6 November 2012 Pilot s Operating Handbook Section 922 EXTRA 300LT XTRA GARMIN GTN 635 650 750 B DEAD RECKONING MODE If the amber Dead Reckoning DR Mode message is displayed the course guidance will be removed from the CDI The airplane position will be
60. unit to set the Squelch level automatically When enabled the Auto Squelch key will display a green bar 6 Touch the Squelch arrows to set the desired Squelch level 7 Touch the Back key to return to the Intercom Setup page 8 Touch the Music 1 or Music 2 keys to set their configuration 9 Select the recipients for Music Distribution by touching any combination of the Pilot and Co Pilot keys 10 Touch the Radio and or Intercom keys to select the function that when active Music will be muted 11 Touch the Volume arrows to set the desired Volume level 922 7 6 POWERING UP THE GTN 635 650 750 The GTN 635 650 750 power and COM volume are controlled using the power volume knob atthe top left corner of the unit Turning it clockwise will turn unit power on and increase the COM radio volume After turning the unit on several system startup pages will be displayed A copyright page asoftware amp database versions and dates page and a self test page The database confirmation page shows the current database information onthe NavData card with the valid operating dates cycle number and database type indicated The database is updated every 28 days and mustbe current Information on database subscriptions is available inside your GTN 635 650 750 package 922 14 Page Date 6 November 2012 Pilot s Operating Handbook Section 922 EXTRA 300LT XTRA GARMIN GTN 635 650 750 To acknowledge or advance to the next page to
61. will fail the attitude solution posta red X in place of the attitude and heading information and present 917 6 Page Date 6 November 2012 Pilot s Operating Handbook Section 917 EXTRA 300LT XTRA ASPENEFD1000 500 System a CHECK PITOT HEAT message as a reminder to the pilot to check for ice accumulating on the pitot probe An ATTITUDE FAIL annunciation will accompany the CHECK PITOT HEAT amber annunciation and will be presented when indicated airspeed is less than 30 KIAS 35 mph and GPS groundspeed is greater than 50 kts 58 mph NOTE The EXTRA 300LT doesn t feature a pitot heating system So the CHECK PITOT HEAT amber annunciation shall be taken as a note that a failure of the pitot static system has been detected In this case the following actions shall be performed 1 Select the alternate static source if installed 2 Cross check the readings of the primary airspeed indicator the airspeed indications of the two EFD1000 displays and the GPS generated groundspeed indication to find out which values are corrupt In case of doubt use the visual horizon as a liable reference Once the system detects that the pitot obstruction has been cleared the CHECK PITOT HEAT annunciation is removed and the system automatically performs an ADAHRS in flight reset Should a GPS failure be experienced in flight the Pitot Obstruction Monitor continues to operate in a fail safe mode and will continue to detect o
62. x HOIVIO2SVO JAVA 40193138 Or Nivud se CN OT Wi OF o 16 NVL OMOV 192 JNN LINIA 3 HY ANVL ONIM HY MOAN Y3 14 Figure 3 Fuel System 7 11 Page Date 6 April 2010 Section 7 Neu Pilot s Operating Handbook Description and Operation of Aircraft and Systems X TRA EXTRA 300LT Wing Tank The wing provides an integral fuel tank compartment on each side located behind the main spar with a capacity of 76 liters 20 1 US Gal each Each side of the wing has a 2 diameter filler cap for gravity refueling Unusable fuel of each tank is 5 liters 1 3 US Gal 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 60 liters 15 9 US Gal in front of the main spar of the wing The Acro tank is connected with the center tank in a gravity feed system The center tank has a 2 diameter filler cap for gravity refueling Unusable fuel is 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
63. 09 EXTRA 300LT XTRA ARTEXME 406 ELT 909 1 GENERAL Toimprovethe passive security the EXTRA 300LT can be equipped with an optional Emergency Locator Transmitter ARTEX ME 406 Inthe eventof acrash the ME 406 activates automatically automatic fixed AF configuration and transmits the standard swepttone on 121 5 MHz lasting until battery poweris gone This 121 5 MHz signalis mainly used to pinpointthe beacon during search and rescue operations In addition for the first 24 hours of operation a 406 MHz signal is transmitted at 50 second intervals This transmission lasts 440 ms and contains identification data programmed into the beacon and is received by Cospas Sarsat satellites Thetransmitted data is referenced in a database maintained bythe national authority responsible for ELT registration and usedto identifythe beacon and owner When the ELT is activated the buzzer beeps and the panel LED pulses periodically The time between pulses lengthen after a predetermined transmitter on time NOTE In October 2000 the International Cospas Sarsat Program announced at its 25th Council Session held in London UK that it plans to terminate satellite processing of distress signals from 121 5 and 243 MHz emergency beacons on February 1 2009 Accuracy Doppler positioning is employed using both 121 5 MHz and 406 MHz signals Position accuracy ofthe 121 5 MHz signalis within an area of approximately 15 20 km radius about the tra
64. 10 Pilot s Operating Handbook Section 906 EXTRA 300LT XTRA Digital RPM Indicator OPERATION BUTTONS There are three panel buttons Each button has two modes of operation PRESS AND HOLD operation mode press and hold for more than 2 3 of a second Thisoperation mode is placarded above each button Hours Clear Trap Engine time Hours The left button upon depression will cause the tachometer to display the non fractional portion 0000 of the current accumulated engine hours When the button is released the fractional part of the engine hours 00 is displayed for a short period of time The clock is started whenever the engine rpm exceeds 800 rpm and is recorded in real hours Clear Clear The middle button clears the rpm trap During depression of the switch the rpm trap is zeroed When the button is released the trap will record the current engine rpm Engine rpm Trap The right button will cause the tachometer to display the current contents of the rpm trap This trap records the highest engine rpm achieved 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 rema
65. 12 Economy 2000 23 8 55 173 43 2 11 4 149 276 152 281 3 96 591 1094 Economy 2000 20 7 45 142 37 1 9 8 131 243 134 249 4 61 604 1119 Economy 2000 2700 28 7 98 309 98 0 25 9 204 377 200 370 1 76 356 659 Power 610 2600 27 0 90 284 85 2 22 5 196 363 193 357 2 02 394 729 Power 2400 24 8 75 236 69 9 18 5 180 333 177 328 2 45 439 814 Power 2200 24 1 65 205 51 5 13 6 167 309 164 305 3 31 551 1020 Economy 2000 23 3 55 173 43 2 11 4 151 280 150 277 3 94 594 1100 Economy 2000 20 3 45 142 37 1 9 8 132 245 132 244 4 58 607 1123 Economy 4000 2700 26 0 91 285 85 6 22 6 200 371 191 354 2 03 399 740 Power 1219 2600 26 8 90 284 85 2 22 5 200 370 191 353 2 04 400 741 Power 2400 24 2 75 236 69 9 18 5 183 338 175 324 2 46 445 825 Power 2200 23 6 65 205 51 5 13 6 169 313 162 300 3 31 555 1028 Economy 2000 22 8 55 173 43 2 11 4 153 283 147 273 3 92 597 1106 Economy 2000 20 0 45 142 37 1 9 8 134 247 130 240 4 55 609 1127 Economy 6000 2700 23 9 83 261 78 9 20 8 195 361 181 336 2 20 421 779 Power 1829 2600 22 5 75 236 71 3 18 8 185 343 173 320 2 42 442 818 Power 2400 21 5 65 205 51 5 13 6 171 317 160 296 3 30 559 1036 Economy 2000 22 4 55 173 482 11 4 154 286 145 268 3 90 600 1111 Economy 2000 19 4 45 142 37 1 9 8 135 250 127 236 4 52 610 1130 Economy 8000 2700 21 5 75 236 73 4 19 4 188 348 170 315 2 36 434 805 Power 2438 2400 21 1 65 205 51 5 13 6 1
66. 17 7US gal For acrobatic flight wing tanks must be empty Page Date 6 April 2010 2 3 Section 2 2 Pilot s Operating Handbook Limitations XTRA EXTRA 300LT 2 4 2 ENGINE LIMITATIONS a Rotational Speed Maximum Take Off and Maximum Continuous 2700 rpm b Oil temperature Maximum 118 C 245 F C Oil capacity Maximum sump capacity 15 13L 16 US qt Minimum sump capacity 8 51L 9 US at d Oil pressure Minimum ldling 172kPa 25 psig Normal 379 655kPa 55 95 psig Starting Warm up Taxi and Take Off 793 kPa 115psig N CAUTION lt is normal for the oil pressure to flicker from 69 to 207 kPa 10 to 30 psig 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 W NNC If oil pressure drops to 0 kPa psig 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 atfuel flow divider Maximum 97 kPa 14 psig f Cylinder head temperature Max 241 C 465 F 2 4 Page Date 6 April 2010 Pilot s Operating Handbook Section 2 EXTRA 300LT XTRA Limitations 2 5 PROPELLER MT Propeller Entwicklung GmbH Federal Republic of Germany Type MTV 9 B C C198
67. 2 9 VER Gode eru EE EE EE EO RE OR 912 10 Configuration MODS EE N Segen 912 10 LIMITATIONS ii osse ees Ee eer a tev GE Pg a ee eg ee ee 912 10 EMERGENCY PROCEDURES sie es ek esse ee Ge be eed ede ca ee ee bekas DE 912 10 Important ee EE 912 10 NORMAL PROCEDURES ee EE ee ee ed ee ee ee 912 10 PERFORMANCE ie EE 912 10 Page Date 6 April 2010 912 1 Section 912 Pilot s Operating Handbook BECKER BXP 6401 Transponder XTRA EXTRA 300LT Left blank intentionally 912 2 Page Date 6 April 2010 Pilot s Operating Handbook Section 912 EXTRA 300LT XTRA BECKER BXP 6401 Transponder 912 1 GENERAL The Becker panel mounted BXP 6401 Transponderis a radio transmitter and receiver that fulfills the role of the airborne beacon equipment according to the requirements of the Air Traffic Radar Beacon System ATCRBS Its functionality includes replying to ATCRBS Mode A C and Mode S interrogations It operates on radar frequencies receiving ground radar interrogations at 1030 MHz and transmitting a coded response of pulses to ground based radar on a frequency of 1090 MHz The BXP 6401 is equipped with IDENT capability that activates the Special Position Identification SPI pulse NOTE The BXP 6401 owner accepts all responsibility for obtaining the proper license before using the transponder Refer to Becker Pilot s Guide Page Date 6 April 2010 912 3 Section 912 Pilot s Operating Handbook BECKE
68. 25 Maximum rotational speed Take Off and Maximum Continuous 2700 rpm 2 6 WEIGHT LIMITS Max allowed empty weight Normal category 723 kg 1594 Ibs Acrobatic category III 742 kg 1636 Ibs Acrobatic category II 662 kg 1460 Ibs Acrobatic category 686 kg 1513 Ibs Max allowed T O weight Normal category amp Acrobatic category III 950 kg 2095 Ibs Acrobatic category II 870 kg 1918 Ibs Acrobatic category 820 kg 1808 Ibs Max allowed landing weight 950 kg 2095 Ibs 2 7 WEIGHT AND C G ENVELOPE Vertical reference fire wall Horizontal reference upper longerons in cockpit Straight lines between limits 2 7 1 NORMAL CATEGORY AND ACROBATIC CATEGORY III 2 SEATS Weight forward C G rear C G 950 kg 2095 Ibs 73 0 cm 28 7 84 1 cm 33 1 915 kg 2017 Ibs 88 0 cm 34 6 820 kg 1808 Ibs 70 7 cm 27 8 88 0 cm 34 6 and below 2 7 2 ACROBATIC CATEGORY I 2 SEATS Weight forward C G rear C G 870 kg 1918 lbs 71 6 cm 28 2 88 0 cm 34 6 820 kg 1808 Ibs 70 7 cm 27 8 88 0 cm 34 6 and below 2 7 3 ACROBATIC CATEGORY I 1 SEAT Weight forward C G rear C G 820 kg 1808 Ibs 70 7 cm 27 8 88 0 cm 34 6 and below Page Date 6 April 2010 2 5 Section 2 Pilot s Operating Handbook Limitations XTRA EXTRA 300LT 2 8 ACROBATIC MANEUVERS 2 8 1 NORMAL FLIGHT All acrobatic maneuvers are prohibited except stall chandelle lazy eight and turns u
69. 3 MHz emergency beacons on February 1 2009 ACCURACY Doppler positioning is employed using both 121 5 MHz and 406 MHz signals Position accuracy ofthe 121 5 MHz signalis within an area of approximately 15 20 km radius about the transmitter Due to the better integrity ofthe 406 MHz signal its location accuracy is within about a 3 km radius 924 2 LIMITATIONS The operation limitations are not affected by the installation of the KANNAD AF 406 COMPACT or INTEGRAELT For the operation of the transmitter the following placard is on the front face of the remote switch 3 ES y S i on the ELT remote switch E S ST Jg Page Date 22 April 2015 924 3 Section 924 Pilot s Operating Handbook KANNAD AF 406 ELT XTRA EXTRA 300LT 924 3 EMERGENCY PROCEDURES e Incase of a forced landing switch the remote switch in the rear instrument panel to the ON position prior to touch down Although the ELT will be activated automatically after an aircraft accident or forced landing with high G force Switch additionally the remote switch in the rear panel to the ON position After sighting rescue aircraft Switch the remote switch to the ARM position to prevent radio interference e Attempt contact with rescue aircraft with the radio transceiver set to a frequency of 121 5 MHz If no contact is established switch the remote switch to the ON position immediately If the function of the rem
70. 300LT X TRA Description and Operation of Aircraft and Systems 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 AEIO 580 B1A engine is characterized by the following performance data Rated power at 2700 RPM 315 HP 234 9 kW Rated power at 2600 RPM 303 HP 225 9 kW Rated power at 2400 RPM 286 HP 213 3 kW The engine is equipped on the left side with a retard type magneto This magneto has a retard breaker providing a fixed retard and long duration boosted spark for starting A Slick Start System completes the installation For the present TBO refer to latest issue of Textron Lycoming SERVICE LETTER No L 201 The AEIO 580 B1A engine is equipped with special antivibration counterweights The following accessories are included in the power plant installation Fuel Injector Magnetos Start System Alternator Starter Fuel pump Shielded ignition system Propeller governor drive The engine is operated with the following manual controls Throttle control dual RPM control Fuel mixture control The propeller governor monitors the RPM automatically and prevents overspeeding In the event that oil pressure is lost the propeller is automatically adjusted to coarse pitch in order to avoid overspeeding The use of 100 130 aviation grade fuel AV
71. 32 F Roll 50 ft 10 C 50 F Roll 50ft 20 C 68F Roll 50ft 30 C 86F Roll 50 ft 40 C 104 F Roll 50 ft SL 2000 610 4000 1219 6000 1829 8000 2438 10000 3048 528 585 648 720 833 963 1619 1792 1987 2207 2553 2953 575 637 706 784 907 1049 1763 1952 2164 2403 2780 3215 624 691 766 851 984 1139 1913 2119 2349 2609 3017 3490 676 748 829 921 1065 1232 2071 2293 2543 2824 3266 3778 729 807 895 994 1150 1330 2235 2475 2744 3048 3525 4078 785 869 964 1070 1238 1432 2406 2665 2955 3281 3795 4390 843 934 1035 1150 1330 1538 2585 2862 3173 3524 4076 4715 Page Date 6 April 2010 ii M EXTRA SECTION 6 WEIGHT amp BALANCE amp EQUIPMENT LIST Table of Contents Paragraph Page 6 1 GENERAL S 6 3 6 2 AIRCRAFT WEIGHING PROCEDURE ees esse seen see ee ee aa ae ee RR ee RR Re RARR Rae RR RE Re AR RE Ee ee ARK Rae REKE 6 3 6 2 1 Owners Weight and Balance Record issie ee ee ee RA Re ee Ge cnn ee RA eke ee ee ee ee 6 4 6 3 CENTER OF GRAVITY CALCULATION SAMPLE PROBLEM eee 6 5 6 3 1 Se AR H OE 6 7 6 3 2 Weight and Balance Record Sheet AA 6 7 6 4 LOADING WEIGHTS AND MOMENT sees eens e ee ees ee RE Re RARR Rae RR KERR EE EER AAR RR Gee RR nc 6 8 6 5 WEIGHTS AND MOM
72. 5 2 US gal Usable fuel capacity for acrobatic 67 L 17 7 US gal Maximum sump capacity 15 13L 16US qt Minimum sump capacity 8 51L 9US qt Average ambient air Mil L6082 Mil 22851 temperature grades ashless dispersant grades Alltemperatures SAE 15W50 or 20W50 27 C 80 F SAE 60 gt 16 60 F SAE 40 or 60 1 C til 32 C SAE 40 30 F 90 F Page Date 6 April 2010 1 5 Section 1 2 Pilot s Operating Handbook General m XTRA EXTRA 300LT 1 7 OIL Cont Average ambientair Mil L6082 Mil 22851 temperature grades ashless dispersant grades 18 til 21 C SAE 30 SAE 30 40 or 20W40 0 F 70 F 18 C til 32 C SAE 20W50 SAE 20W50 or 15W50 0 F 90 F lt 12 10 F SAE 20 SAE 30 or 20W30 single or multi viscosity aviation grade oils see latest issue of Textron Lyc S l No 1014 1 8 LOADING Wing loading MTOW Normal Acrobatic IIl 87 64 kg m 17 95 lbs ft Acrobatic lI 80 26 kg m 16 44 lbs ft Acrobatic 75 65 kg m 15 50 lbs ft Power loading MTOW Normal Acrobaticlll 4 04 kg kW 6 65 lbs hp Acrobatic II 3 70 kg kW 6 09 Ibs hp Acrobatic 3 49 kg kW 5 74 lbs hp 1 9 TERMINOLOGY Air Speeds CAS Calibrated Air Speed CAS is the same as TAS True Air Speed in standard atmospheric condition at sea level KCAS Calibrated speed in knots GS Ground speed IAS Indicated air speed KIAS Indicated speed in knots TAS True air speed It s the same as CAS compensated fo
73. 7 2 910 7 3 SECTION 910 NAT AA83 001 INTECOM Table of Contents Page GENERAL ai eege ee RE GR AE 910 3 Installation Adj stmients OE RE N 910 3 El BEN le OM EE EE OE N EE N EO EE 910 3 EMERGENCY PROCEDURES aaaaaaaaaaaaaaaaaa nnnnnannnnnnnnnnanannannnnnnnunnnnnnnnnunnannanann nana 910 4 NORMAL PROCEDURES cesses eese ee ese ek ee Gee EK ek Gee RR R4 SNR RR RR SNR KA RR ARN ra ama EE Ke 910 4 PERFORMANCE iia EE EE EE EE 910 4 WEIGHTAND BALANCE ee iria illa 910 4 SYSTEM DESCRIPTION ees see ees see ee ee Ak ee EK Ak Ee Ke Ee KA nan nana carac nar rr aaa KA Gee 910 4 Controls and Indicators ee ee ee ed ee danan ee ee ee ee ee ee ee ee ee stress nnl 910 4 Bee N 910 6 AONA OA e oe ee A n e De A 910 7 Page Date 6 April 2010 910 1 Section 910 Pilot s Operating Handbook NAT AA83 001 Intercom XTRA EXTRA 300LT Left blank intentionally 910 2 Page Date 6 April 2010 Pilot s Operating Handbook XTR A m 910 ed ntercom EXTRA 300LT 910 1 910 1 1 910 2 GENERAL The AA83 001 is a stereo voice activated intercom providing full intercom capabilities for pilot and copilot Further passenger features are not used in the configuration installed The AA83 001 also provides transmit capability for pilot and co pilotto a single COM radio or audio selector panel The AA83 001 accepts stereo music inp
74. 73 321 157 291 3 29 563 1042 Economy 2050 21 5 55 173 43 2 11 4 156 289 142 263 3 88 602 1116 Economy 2000 19 2 45 142 37 1 9 8 136 252 125 281 4 49 612 1133 Economy 10000 2700 19 4 67 211 68 4 18 1 178 330 157 292 2 52 441 817 Power 3048 2600 19 4 65 205 51 5 18 6 175 325 155 287 3 27 565 1047 Economy 2200 19 4 55 173 43 2 11 4 158 292 140 259 3 85 604 1118 Economy 2000 18 7 45 142 37 1 9 8 137 254 122 227 4 45 612 1133 Economy 1 Fortemperatures above below Standard ISA increase decrease Range 1 7 and Endurance 1 1 for each 10 C 18 F above below Standard Day Temperature for particular altitude 2 Leaning with exhaust gas temperature EGT gage For the adjustment Best Power first lean the mixture to achieve the top exhaust tempe rature peak EGT and then enrich again until the exhaust temperature is 100 F lower than peak EGT For the adjustment Best Economy simply lean the mixture to achieve the top exhausttemperature peak EGT YN CAUTION Always return the mixture to full rich before increasing power settings Page Date 6 April 2010 5 15 Section 5 Performance XTRA Pilot s Operating Handbook EXTRA 300LT 5 12 TIME DISTANCE FUEL TO DESCENT Example Cruise at 8000 ft 2438m Press Alt Descent to 2000 ft 610m Press Alt Time to descend 8 2 6 min Fuel to descend 4 1 3 Liter Distance to descend
75. 80 km h OAT gt 20 C A F 10 C 14 OC 32F 10 C 50 20 C 68 30 C 86 40 C 104 F PA ft m Roll 50ft Roll 50ft Roll 50ft Roll 50ft Roll 50ft Roll 50ft Roll 50ft SL 161 493 175 537 190 583 206 631 222 681 239 733 257 788 2000 610 178 546 194 595 211 646 228 699 246 754 265 812 285 872 4000 1219 198 606 215 660 234 716 253 775 273 836 294 901 316 967 6000 1829 219 673 239 733 259 795 281 861 303 929 326 1000 350 1074 8000 2438 254 778 276 847 300 920 325 995 350 1074 377 1157 405 1242 10000 3048 294 900 320 980 347 1064 376 1151 405 1243 436 1338 469 1437 Page Date 6 November 2012 5 17 Section 5 Performance XTRA Pilot s Operating Handbook EXTRA 300LT Landing distance in feet for landing roll Roll and landing distance over 50 ft obstacle 50 ft Weight 820 kg 1808 Ibs approach speed 79 KIAS 146 km h OAT gt PA ft m 20 C 4F Roll 50 ft 10 C 14 Roll 50 ft 0 C 32 F Roll 50 ft 10 C 50 Roll 50ft 20 C 68F Roll 50ft 30 C 86F Roll 50ft 40 C 104 F Roll 50 ft SL 2000 610 4000 1219 6000 1829 8000 2438 10000 3048 430 476 528 586 678 784 1317 1459 1617 1796 2077 2403 468 518 575 638 738 854 1435 1588 1761
76. 85 km h find your airspeed attitude which will keep the fire away from the cockpit 6 Land AS SOON AS POSSIBLE ICING INADVERTENT ICING ENCOUNTER 1 Turn back or change altitude to obtain an outside temperature that is less conductive to icing 2 Plan a landing at the nearest airfield With extremely rapid ice build up select a suitable off airport landing field UNINTENTIONAL SPIN Refer to section 4 Normal Procedures acrobatic maneuver spin recovery MANUAL BAIL OUT When in an emergency situation that requires abandoning the aircraft and while wearing a parachute which is at least strongly recommended for acrobatics Inform your passenger Reduce speed to 100 KIAS 185 km h if possible Pull mixture to lean Open canopy the low pressure over the canopy in normal flight will flip the canopy full open immediately Takeoff headset Open seat belt Leave airplane to the left side Try to avoid wing and tail Openparachute POND OO OO YO au Page Date 6 April 2010 3 7 Section 3 Pilot s Operating Handbook Emergency Procedures XTRA EXTRA 300LT 3 8 EMERGENCY EXIT AFTER TURN OVER 1 Battery switch OFF 2 Alternator switch OFF 3 Fuelshutoff valve OFF Pull amp Turn 4 Seat belts OPEN 5 Parachute harnesses if wearing a parachute OPEN 6 Canopy handle PULL TO OPEN NOTE If canopy fails to open break the canopy 7 Aircraft EVACUATE ASAP 3 9 ELEVATOR CONTROL F
77. AAR 8 p NAT AA83 001 Intercom esse ee ee ee ER RR EE ER EER RR EE ER KERR RE n nennen nnnnn nans EER EE EER nnn 8 p BECKER ATC 4401 Transponder essei KEER Re AAR ERGE ARK Rae KERE AA nnn nn nnns Rea ee nana 8 p BECKER BXP 6401 Transponder sees eek Ra ee EER Re AAR ERG RARR Re RR RE ERA RE RE Ee ee RR Ra Gee ee 12 p GARMIN GTX 327 Transponder esse ee see EER RE AAR RR RR nennen nnne Rae nennen ER EE nannten 6 p GARMIN GTX 328 Transponder e KERR AAR ERGER KRAKE RE Re AAR RR nnne nn nnn EER AAR RR ae nnn 8 p GARMIN GTX 330 Transponder 1 renonce nei eene eek bee be Week aan Ae 8 p GARMIN GNC 420W GNS 430W ee ee ee Re ER Re Ge RE nennen tnn AR Ee nennen tnn Ge 8 p ASPEN EFD1000 500 System eese Re ER Re ke nnne nnne nein ee Ee ee Re ee 12p aka EE EE id 6 p Reserved ci ccccssecce cy cacues fete acessdud eed seeiedcenscesenteddesseneseeudueesstuteasexveteveeuecserceeevvedcderse 0p ROSCIV OO E 0p AIRPLANES REGISTERED IN BRAZIL AND OPERATING UNDER THE AGENCIA NACIONAL DE AVIACAO CIVIL REQUIREMENTS sss 6 p GARMIN GTN635 650 750Q SE EERS EN NRS GEKEER WE Rees died ania Ese kk 16 p Page Date 6 November 2012 9 Section 9 Pilot s Operating Handbook Supplements XTRA EXTRA 300LT 923 7 Reserved EE 0 p 924 KANNAD406 AF COMPACT INTEGRA ELT
78. 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 6 April 2010 Pilot s Operating Handbook XIRA EXTRA 300LT SECTION 4 NORMAL PROCEDURES Table of Contents Paragraph Page 4 0 A Pe AN 4 3 4 0 1 Airspeeds for Normal Operation aaaaaaaaaaaasaaas sanasaanannaaansnanannnnnnnnnnnnanansnnnannnnnnnannnnanaai 4 3 4 0 2 Checklist and Pro edures uses tecta teta cuta antena acuta ne rana a Du n dee 4 3 4 1 PREFEIGHT INSPEGTION ii aa 4 4 4 2 CHECKEIST PROCEDURES coria dee 4 4 4 3 STARTING PROCEDURES eege di 4 6 4 3 1 olla j nle AE RE A o RRR 4 6 4 3 2 For Seil 4 6 4 4 TAXIING THE AIRCRAFT socio circo ii ii 4 6 4 5 TAKE OFF ERGOE Eege 4 7 4 5 1 Belore Take Off EE 4 7 4 5 2 Ee iii PT 4 7 4 6 ed EE AE EE EE EA EE N 4 8 4 7 CRUISE EN Ne 4 8 4 8 LANDING PROCEDURES reitera cuerno cce eres ran gedek rana mn aec Dora nane Iu ds ke Ee ek n enr eia Ee ede 4 8 4 8 1 Bree MM m 4 8 4 8 2 Le elt le st 4 8 4 8 3 Before Landini EL EE DP P 4 8 4 8 4 Normal Landing AR EE iii 4 9 4 9 GOAROUND RUE 4 9 4 10 SHUTDOWNE i
79. AR SEAT ONLY In front instrumental panel CALLSIGN In both cockpits For N 030 060 E 120 150 stoor NE N EE EN For S 210 240 W 300 330 E _ Near Mag Dir Indicator Page Date 6 April 2010 2 11 Section 2 Pilot s Operating Handbook Limitations XTRA EXTRA 300LT WING TANK DRAIN Near the LH drain valve in the bottom fuselage cover CENTER TANK DRAIN Near the RH drain valve in the bottom fuselage cover GASCOLATOR DRAIN Near the drain valve on the RH lower side of the firewall USE STRAIGHT MINERAL OIL FOR A MINIMUM OF 50 HOURS On the inside of the separate hatch upper cowling On the outside of the wheel fairings TORQUE TUBE LUBRICATION On the centreline of bottom fuselage cover NO STEP In rear cockpit on the aileron control rods NO HANDHOLD In rear cockpit on the LH side of the panel cover NO BAGGAGE On the FOD protection cover behind the pilot seat Use baggage compartment in Normal Category only Maximum baggage weight 10 kg 22 Ibs Secure baggage with tie down straps and baggage net On the inside of the baggage compartment access door in the upper main fuselage cover In both cockpits on the RH side Page Date 6 April 2010 Pilot s Operating Handbook EXTRA 300LT XTRA Section 2 Limitations Approved acrobatic maneuvers and recommended entry airspeeds
80. AT art ds OVERHEAT While ie word INDICATOR appears flying INDICATOR appears flying EXTRA is prohibited EXTBA is prohibited The standard aircraft is designed to operate within a range of ambient air temperature from 20 C to 44 C 4 F to 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 seats The fuselage except the rear lower part is faired with an aramid carbon laminate shell Within the exhaust area stainless steel sheet metal is used The upper fuselage body surface is one part from firewall to vertical stabilizer including the correlated canopy frame and a baggage compartment which is located aft of the back seat Only the lower rear part of the fuselage is covered with Ceconite 102 The canopy frame itself is constructed by carbon laminate The canopy is one part opens to the right and is held in the open position by a belt Emergency jettisonning is achieved by simply unlatching the canopy For additional pilot protection a roll bar is installed behind the rear pilots seat Page Date 6 April 2010 7 8 Section 7 Neu Pilot s Operating Handbook Description and Operation of Aircraft and Systems X TRA EXTRA 300LT
81. April 2015 924 1 Section 924 Pilot s Operating Handbook KANNAD AF 406 ELT XTRA EXTRA 300LT Left blank intentionally 924 2 Page Date 22 April 2015 Pilot s Operating Handbook Section 924 EXTRA 300LT XTRA KANNAD AF 406 ELT 924 1 GENERAL Toimprovethe passive security the EXTRA 300LT can be equipped with an optional Emergency Locator Transmitter KANNAD AF 406 COMPACT or INTEGRA ELT Inthe event ofacrash the AF 406 activates automatically automatic fixed AF configuration and transmits the standard swept tone on 121 5 MHz lasting until the battery is depleted This 121 5 MHz signal is mainly used to pinpoint the beacon during search and rescue operations In addition for the first 24 hours of operation a 406 MHz signal is transmitted at 50 second intervals This transmission lasts 440 ms and contains identification data programmed into the beacon and is received by Cospas Sarsat satellites The transmitted data is referenced in a database maintained by the national authority responsible for ELT registration and usedto identify the beacon and owner When the ELT is activated the panel LED pulses periodically The time between pulses lengthens after a predetermined transmitter on time NOTE In October 2000 the International Cospas Sarsat Program announced at its 25th Council Session held in London UK that it plans to terminate satellite processing of distress signals from 121 5 and 24
82. B 0 07 0 45 1 Stall Warn Horn EMAG 01600 0 13 1 60 1 Slip Skid Indicator Rieker 1040 Fl0009 0 05 1 60 Optional Primary Flight Display ASPEN 1 EFD1000 Aspen 910 00001 001 1 32 1 55 O 1 CMPilot Aspen 920 00004 001 0 04 1 50 O 1 CMPro Aspen 920 00004 002 0 04 1 50 O 1 RSM w GPS Aspen 910 00003 001 0 91 3 95 O 1 RSM Install bracket Extra EA 86206 10 0 19 3 95 O Optional Multi Function Display ASPEN 1 EFD1000 Aspen 910 00001 001 1 32 1 55 O 1 EFD500 Aspen 910 00001 003 1 09 1 55 O 1 CM EFD 1000 MFD Aspen 920 00004 004 0 04 1 50 O 1 CMEFD 500 MFD Aspen 920 00004 005 0 04 1 50 O 6 12 Page Date 18 June 2013 Pilot s Operating Handbook XTRA Section 6 EXTRA 300LT Weight and Balance and Equipment List QTY ITEM MANUFACTURER MODELNO PART NO WEIGHT ARM INST R kg m O A 1 RSM w o GPS Aspen 910 00003 002 0 91 3 95 O Optional Hour Meters 1 Flight Timer Winter FSZM1510 01605 0 15 1 55 O Optional Clock 1 Digital Clock Astrotech Fl0004 0 14 1 60 O Optional Aerobatics Equipment 1 Aresti Card Holder Extra Assy 0 09 1 66 O 1 Aresti Card H Aspen Extra 86504 004 PG 0 09 1 66 A 1 Sighting Device LH Extra 8D801 030 01 0 37 1 48 O 1 Sighting Device RH Extra 8D801 030 02 0 37 1 48 O Optional Electronic Accelerometer 1 El accelerometer with TL Elec
83. B FUNCTIONS LEFT HANDKEYS AND KNOBS The COM power volume knob controls unit power and communications radio volume Press momentarily to disable automatic squelch control Inthe GPS 420W this control is used only for power The large left knob COM VLOC is used to tune the megahertz MHz value to the left of the decimal point of the standby frequency for the communications transceiver COM or the VLOC receiver whichever is currently selected by the tuning cursor Page Date 6 April 2010 916 5 Section 916 Pilot s Operating Handbook GARMIN GNC 420W GNS 430W XTRA EXTRA 300LT Thesmallleftknob COM VLOC is used to tune the kilohertz kHz value to the right ofthe decimal point ofthe standby frequency forthe communications transceiver COM orthe VLOC receiver whichever is currently selected by the tuning cursor Press this knob momentarily to toggle the tuning cursor between the COM and VLOC frequency fields The COM flip flop key is used to swap the active and standby COM frequencies Press and hold to select emergency channel 121 500 MHz RIGHT HAND KEYS ANDKNOBS Therange key RNG allows you to selectthe desired map scale Use the up arrow side ofthe key to zoom out to a larger area or the down arrow side to zoom in to a smaller area The direct to key provides access to the direct to function which allows you to enter a destination waypoint and establishes a direct course to the selected destination
84. Can be set to AIZDEF with STO button F CHANGING THE FLIGHT NUMBER 1 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 912 8 Page Date 6 April 2010 Pilot s Operating Handbook Section 912 EXTRA 300LT XTRA BECKER BXP 6401 Transponder VFRCODE 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 B to the indication VFR XXXxX 2 First push to button C now left digit of the code is inverted 3 Now the digit can be changed with B 4 Second push to button C now next left digit of the code is inverted 5 The next digit can be changed with B 6 andthe same for next digits 7 Fifth push to button C now again first digit is inverted 8 Changes can be stored with STO button F 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 912 1 8
85. E COMPLETE COMPLETE ADJUST ANDLOCK CLOSE AND LOCK CHECK ON OFF OFF ON ON Page Date 6 April 2010 Section 4 Pilot s Operating Handbook Normal Procedures gt XTRA EXTRA 300LT 4 3 STARTING PROCEDURES 4 3 1 COLDENGINES The following starting procedures are recommended however the starting conditions may necessitate some variation from these procedures 1 Perform pre flight inspection 2 Set propeller governor control to High RPM position 3 Open throttle approximately 1 4 travel 4 Turn boost pump ON 5 Move mixture control to FULL RICH until a slight but steady fuelflowis noted approximately 3 to 5 seconds and return mixture control to IDLE CUT OFF Turn bost pump OFF 6 Engage starter 7 When engine fires release the ignition switch back to BOTH 8 Move mixture control slowly and smoothly to FULL RICH 9 Checkthe oil pressure gauge If minimum oil pressure is notindicated within 30 seconds shut offthe engine and determine trouble 4 3 2 HOTENGINES Because of the fact that the fuel percolates and the system must be cleared of vapor it is recommended to use the same procedure as outlined for cold engine start 4 4 TAXIING THE AIRCRAFT 1 Canopy CLOSE ANDLOCK 2 Brake CHECK 3 Altimeter Set on QFE or QNH Scale error max 60 ft 4 Avionic switch ON 5 Electrical equipment ON 6 Radio Set and test 7 Mixture Leavein FULL RICH position Operate only with the propeller
86. EANING TheClean Screen mode makesthe touchscreen inactive so the display can be manually cleaned The front bezel keypad and display can be cleaned with a microfiber cloth or with a soft cotton cloth dampened with clean water DO NOT use any chemical cleaning agents Care should be taken to avoid scratching the surface of the display While viewing the Utilities page group touch the Clean Screen key to start the Screen Cleaning Mode Touch the HOME key to exit Screen Cleaning Mode Page Date 6 November 2012 922 15 Section 922 Pilot s Operating Handbook GARMIN GTN 635 650 750 XTRA EXTRA 300LT Left blank intentionally 922 16 Page Date 6 November 2012 ET EXTRA SECTION 924 KANNAD 406 AF COMPACT INTEGRA ELT Table of Contents Paragraph Page 924 1 GENERAL iii ia 924 3 924 2 LIMITATIONS e 924 3 924 3 EMERGENCY PROCEDURES lt lt lt lt 0ciiainraiciicidid ica 924 4 924 4 NORMAL PROCEDURES etta annt AE NE inicia 924 4 924 5 PERFORMANCE 924 5 924 6 WEIGHT amp CENTER OF GRAVITY eere dara adaa duran n ansa RR GER Ge KEER EN Eed 924 5 924 7 SYSTEM DESCRIPTION 2 73 tide oie lada N ee Vanga n a 924 5 924 7 1 lee te N ER EEN 924 6 924 8 HANDLING SERVICING AND MAINTENANCE ee esse see ese ee ese ee ee ee nnne nnne 924 6 924 8 1 Periodi spel EE 924 6 924 8 2 Battery ste ele Sn LG EE EE Phi encore EE fiat 924 7 Page Date 22
87. ENTS LIMITS sees sesse see n Rae eek Rae RR Re RARR Re RARR cnn 6 9 6 6 EQUIPMENT LIST EE EE N N EN 6 10 Page Date 6 April 2010 6 1 Section 6 Pilot s Operating Handbook Weight and Balance and Equipment List XTRA EXTRA 300LT Left blank intentionally 6 2 Page Date 6 April 2010 Pilot s Operating Handbook Section 6 EXTRA 300LT Perd 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 AIRCRAFTWEIGHING PROCEDURE The aircraft weight is determined by weighing all three wheel loads simultaneously by three scales with the aircraft levelled Upper fuselage reference line horizontal Datum line for weight arms x is the fire wall X1 distance fire wall main wheel X2 distance fire wall tail wheel XN distance fire wall item N XG distance fire wall Center of Gravity W1 Sum of weights indicated by the two scales below the main wheels W2 Weight indicated by the scale below the tail wheel W Total weight W1 W2 XG W1x X1 W2 x X2 CG position W Reference Fi
88. ERGENCY PROCEDURES rosserae kk S Ge es kk GEN NG ee ie GEK Ke eed RAR 904 3 NORMAL PROCEDURES ee n ne ee ee ee KEN N Mee ee eN KEN N NEG R WEE Be GEN ana a an ee eN KEN N NEG See EN N NE 904 3 PERFORMANCE m 904 3 WEIGHT AND BALANCE iii a A xn ure cer yx aou C 904 4 DESCRIPTION M EE EE R RAR SKAR 904 4 Page Date 6 April 2010 904 1 Section 904 Pilot s Operating Handbook Accelerometer TL 3424 EXT X TRA EXTRA 300LT Left blank intentionally 904 2 Page Date 6 April 2010 Pilot s Operating Handbook Section 904 EXTRA 300LT X TRA Accelerometer TL 3424 EXT 904 904 1 904 2 904 3 904 4 904 5 ACCELEROMETERTL 3424 EXT GENERAL The TL 3424 EXT accelerometer can be installed as an option in the 300LT Itis usedin a special password protected configuration This configuration helps the pilot to operate the aircraft within limits In detailthe TL 3424 EXT accelerometer allows 1 displaying current acceleration values 2 displaying the minimum and maximum acceleration 3 recording of all acceleration and speed values into the long term memory 4 recording of any exceedance of limits 5 warning the pilot before reaching load limits by a sound to hear on the head set 6 indicating to the pilot when he has exceeded a load or speed limit by a sound on the head set and the G V LIMITS WARNING LIGHT and 7 transferring
89. GAS 100 is the minimum grade recommended by the manufacturer ofthe AEIO 580 B1A engine For continuous operation 115 145 aviation fuel is the maximum grade 7 10 2 OIL SYSTEM The oil is cooled by a Single Cooler System The oil cooler is mounted on the aft right hand side of the engine The oil level is determined by a dip stick A thermostatic valve is fitted upstream of the oil cooler This valve ensures a quick warm up of the oil after engine start Oil capacity and grades Max sump capacity 16 gts Min sump capacity 9 qts For temperatures and oil grades refer to Section 1 7 Page Date 6 April 2010 7 9 Section 7 Neu Pilot s Operating Handbook Description and Operation of Aircraft and Systems X TRA EXTRA 300LT 7 10 3 ENGINE INSTALLATION The engine is supported by four shock mounts type LORD or BARRY CONTROLS to the tig welded steel tube engine mount which is attached to the fuselage with four bolts on the firewall axis The engine cowling is divided into two parts a lower and an upper part both made of glass fibre carbonfibre reinforced epoxy The parts are fixed by a number of screws and the upper cowling has a separate hatch for easy access to the oil dip stick 7 10 4 PROPELLER The standard propeller is a 3 blade wood composite constantspeed MTV 9 B C C 198 25 type propeller The propeller has a diameter of 1 98 m 77 95 in 7 10 5 THROTTLE Dual control mounted on the left side of the cockp
90. GTX 330 Transponder is automatically powered on by the respective AVIONIC switch or when previously manually powered off while AVIONIC switch is on by pressing the STBY ALT or ON keys After power on a start up page will be displayed while the unit performs a self test This supplement is written for software version 3 00 or later andis not suitable for earlier software versions Some differences in operation may be observed when comparing the information in this supplementto later software versions Verify the information herein with the GTX 330 pilot s guide PN 190 00207 00 applicable revision you received with yourtransponder Page Date 6 April 2010 915 3 Section 915 Pilot s Operating Handbook GARMIN GTX 330 Transponder XTRA EXTRA 300LT 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 transponder replies to identification and altitude interrogations as indicated by the Reply Symbol Replies to altitud
91. KER ATC 4401 Transponder 911 1 GENERAL The Becker panel mounted ATC 4401 Transponderis a radio transmitter and receiver that fulfills the role of the airborne beacon equipment according to the requirements of the Air Traffic Radar Beacon System ATCRBS Its functionality includes replying to ATCRBS Mode A and Mode C interrogations It operates on radar frequencies receiving ground radar interrogations at 1030 MHz and transmitting a coded response of pulses to ground based radar on a frequency of 1090 MHz The 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 6 April 2010 911 3 Section 911 BECKER ATC 4401 Transponder Pilot s Operating Handbook EXTRA 300LT XTRA CONTROLS AND INDICATORS OFF SBY ON ALT rotary mode switch with 4 detent positions OFF position Transponder is switched off expect panel lighting SBY position Standby mode is switched on ON position Mode A is switched on ALT position Mode A C is switched on Rotary coding switch with 8 detents positions continuously rotable Control of the cursor in one of the 4 code digits or from the display field Rotary coding switch with 8 detents positions continuously rotable Setting the code digits from 0
92. LATION OPERATION In normal operation the pilot and copilot hear the same signals from the aircraft communication system Sometimes this is not desirable from the pilot s perspective for instance during communication with the tower on approach or when discussions on the intercom would be a distraction Many times the copilot position is simply another passenger and the pilot may wish to be isolated from him PILOT ISO mode separates the radio communications without pilot from the intercom network allowing confidential interference from the copilot intercom or music The pilot has no ICS operation and all signals are presented in mono format during this mode The other user is unaffected and continues to use the entertainment functions of the AA83 001 While in PILOT ISO mode the pilot maintains complete control of all the radio functions of the intercom and the pilot mic and TX keyline are directly connected to the transceiver The pilot phones are driven by the transceiver 910 6 Page Date 6 April 2010 Pilot s Operating Handbook Section 910 EXTRA 300LT XTRA NAT AA83 001 Intercom The copilot will be unable to monitor any transceiver activity although he retains full ICS and music functions This mode is fail passive meaning that it requires no power to operate and is the same mode the box goes into automatically when power is lost to the AA83 001 In this way switch over is immediate for the pilot and there is
93. LT 922 6 WEIGHT amp CENTER OF GRAVITY Refer to the equipment list in Section 6 of this Handbook 922 7 SYSTEMDESCRIPTION 922 7 1 TOUCHSCREEN KEY AND KNOB FUNCTIONS Controls are a combination of a dual concentric rotary knob and push keys on the bezel with the color display providing information as well as active touch areas on the display TOUCHSCREEN The GTN 635 650 750 units feature a touch panel thatprovides a visual display of both controls and functions The required controls are displayed forthe selected function Keys on the display allow you to access and control their functions by touching the interactive display A list of menu items may be scrolled by touching the screen and retaining pressure while sliding your finger up or down Mapdisplays may be panned by touching the screen and retaining pressure while sliding your finger in the desired direction Touchscreen keys are placed at the lower portion of the display The keys vary depending on the page selected Touch the key to perform the function or access the described information You can return to the previous page or exit the current function by touching the Back key KEYS Quickly return to the Home page by pressing the HOME key Press and hold the HOME key to reach the Map page The Direct_To key provides access to the direct to function which allows you to enter a waypoint and establishes a direct course to the selected destination KNOBS The Volu
94. NEPOWER 1 Seat belts shoulder harnesses SECURE 2 Airspeed 85 KIAS 157 km h 3 Selected field FLY OVER noting terrain and obstructions then reaching a safe altitude and airspeed 4 Battery switch OFF 5 Alternator switch OFF 6 Touchdown SLIGHTLY TAILLOW 7 Ignition switch OFF 8 Mixture IDLE CUT OFF 9 Fuel shutoff valve OFF Pull amp Turn 10 Brakes APPLY HEAVILY 3 4 FIRES 3 4 1 DURING START ON GROUND 1 Cranking CONTINUE to geta start which would suck the flames and accumulated fuel through the air inlet and into the engine 2 Fuel shutoff valve OFF Pull amp Turn 3 Power 1700 RPM for one minute 4 Engine SHUT DOWN 5 After engine stop ABANDONaircraft and inspect for damage 6 Fire EXTINGUISH usingfire extinguisher if available W NNC Do not open engine compartment access doors while engine is on fire 3 4 2 IF ENGINE FAILS TO START 1 Cranking CONTINUE 2 Throttle FULL OPEN 3 Mixture IDLE CUT OFF 4 Fuel shutoff valve OFF Pull amp Turn If fire is extinguished 5 Battery switch OFF 6 Alternator switch OFF 7 Ignition switch OFF 8 Engine compartment INSPECT 3 6 Page Date 6 April 2010 Pilot s Operating Handbook LL Section 3 EXTRA 300LT XTRA Emergency Procedures 3 4 3 3 5 3 5 1 3 6 3 7 ENGINE FIRE IN FLIGHT 1 Mixture IDLECUTOFF 2 Fuelshutoffvalve OFF Pull 8 Turn 3 Battery switch OFF 4 Alternator switch OFF 5 Airspeed 100 KIAS 1
95. O On the rear instrument panel beneath the acro amp center tanks fuel capacity indicators WING TANK INDICATION SHOWS ZERO IN LEVEL FLIGHT BELOW 10 L 2 6 US GAL On the rear instrument panel beneath the wing tank fuel capacity indicators ACROBATIC 10 G 1 Pilot MTOW 820 kg 1808 Ibs 8 G 2 Persons on board MTOW 870 kg 1918 Ibs 6 G 2 Persons on board MTOW 950 kg 2095 Ibs In both cockpits NORMAL 6G 3G MTOW 950 KG 2095 LBS ACROBATICS INCL SPIN NOT APPROVED In both cockpits In both cockpits USE OF HEADSET IS REQUIRED USE OF PARACHUTE IS RECOMMENDED On the right side of both instrument panels 2 10 Page Date 6 April 2010 Pilot s Operating Handbook E Section 2 EXTRA 300LT XTRA Limitations LOW RPM PROP HIGH RPM On RPM control in the rear cockpit LEAN MIXTURE RICH On mixture control in the rear cockpit CLOSE THROTTLE OPEN Near throttle control in both cockpits CANOPY LOCK LOCK gt UNLOCK e near canopy locking handles of each cockpit qp VENT OPEN Near the eyeball type adjustable vents CAUTION Particular caution must be exercised when performing maneuvers at speeds above Va Large or abrupt control inputs above this speed may impose unacceptably high loads which exceed the structural capability ofthe aircraft In both cockpits WARNING SOLO FLYING FROM RE
96. OE EE N 914 7 NORMAL PROCEDURES eisereen geed 914 7 PERFORMANCE 914 7 Page Date 6 April 2010 914 1 Section 914 Pilot s Operating Handbook GARMIN GTX 328 Transponder XTRA EXTRA 300LT Left blank intentionally 914 2 Page Date 6 April 2010 Pilot s Operating Handbook Section 914 EXTRA 300LT XTRA GARMIN GTX 328 Transponder 914 1 GENERAL The Garmin GTX 328 panel mounted Mode S VFR Transponderis a radio transmitter and receiver that fulfills the role ofthe airborne beacon equipment according to the requirements ofthe Air Traffic Radar Beacon System ATCRBS Its functionality includes replying to ATCRBS Mode A and C and Mode S interrogations The Mode S function will allow the ground station to individually select the aircraft by its Aircraft Address assigned to the aircraft by the aviation agency Itoperates onradar frequencies receiving ground radar interrogations at 1030 MHz andtransmitting a coded response of pulses to ground based radar on a frequency of 1090 MHz The GTX 328 is equipped with IDENT capability that activates the Special Position Identification SPI pulsefor 18 seconds Mode S transmit receive capability also requires 1090 MHz transmitting and1030 MHz receiving for Mode S functions In addition to displaying the code reply symbol and mode of operation the GTX 328 screen will display pressure altitude and timer functions The disp
97. ON NOTE This list may be modified by the minimum eduipment reduirements of individual certifying authorities Page Date 22 April 2015 7 7 Section 7 Neu Pilot s Operating Handbook Description and Operation of Aircraft and Systems X TRA EXTRA 300LT 7 6 2 INSTRUMENT PANEL FRONT COCKPIT Normally the instument panel in the front cockpit is only equipped with Airspeed indicator Altimeter indicator 7 7 LANDING GEAR Thelanding gearis a composite construction with a multichamber fiberglass spring in atail wheel design The main wheels have a size of 5 5 50 and they are equipped with hydraulic disc brakes To reduce aerodynamic drag carbonfiber wheel fairings are installed They feature a submerged airintake for brake disc cooling and a small hatch to reach the valve ofthe wheel tube for inflation The tail wheel has a solid rubber tire with full swivel capability 7 8 SEATS SEAT BELTS The seats are ergonomically shaped composite designs The rear seat angle can be adjusted on the ground with 2 quickpins there are different seat angle possibilities The back rest is also adjustable on the ground in different positions and angle The rear pedal to seat distance can be varied in different positions In the front cockpit there is no possibility to adjust either the pedals nor the seat The seat belt assembly consists of a left and a right shoulder strap two left and two right lap belts and a negative g s
98. PROCEDURES 551 5 1d ee ds eed Ke ds eed Gee veas annee ck Y ka NRK KRANAR 903 3 903 5 PERFORMANCE uuu A eee 903 3 903 6 WEIGHT amp CENTER OF GRAVITY ciiin eene es dd ves diia 903 3 903 7 SYSTEM DESCRIPTION cuina at 903 4 903 8 HANDLING SERVICING AND MAINTENANCE esse see see ees ese ee ee ee ee ee ee ee ee eke ee ee ee 903 4 Page Date 6 April 2010 903 1 Section 903 Pilot s Operating Handbook Cabin Heating System XTRA EXTRA 300LT Left blank intentionally 903 2 Page Date 6 April 2010 Pilot s Operating Handbook Section 903 EXTRA 300LT X TRA Cabin Heating System 903 1 GENERAL The 300LT can be equipped with a cabin heating system which allows feeding the front and rear cockpit independently with warm air The system uses fresh outside air which is heated up by the engine exhaust muffler The system is controlled by two handles in the rear cockpit 903 2 LIMITATIONS The operation limitations are not affected due to the installation of the cabin heat system The following operation placards have to be attached to the aircraft next to the main handle next to the distribution handle 903 3 EMERGENCY PROCEDURES Engine fire Heater OFF 903 4 NORMALPROCEDURES Not affected 903 5 PERFORMANCE Not affected 903 6 WEIGHT amp CENTER OF GRAVITY Refer to the equipment list in Section 6 of this Handbook Page Date 6 Apri
99. R BXP 6401 Transponder XTRA EXTRA 300LT 912 1 1 CONTROLS ANDINDICATORS A Mode Selector Rotary switch with 4 OFF position Transponder is switched off positions SBY position Standby mode is switched on ON position Mode A S is switched on Transmission of altitude information is suppressed ALT position Mode A C S is switched on and the altitude information is transmitted B Rotary switch Rotary optical encoder Rotary switch to change settings rotary mode of C 16 steps per turn C Button Push button Push to jump from digit to digit for settings or from mode of B one menu to the next generally used as an enter key D IDT Push button Activates the Special Identifier SPI in ad dition to the reply code for approx 18 seconds during this time ID appears in the LC display E Display part 1 2 line LCD display Displays the following informations code indication in the top row flight level in the bottom row various informations in the bottom row additional indicators on the left side see Ref H F ISTO Push button Stores the selected values to the settings G SEL Push button Opens and selects the menu H Display part 2 LCD indicators Displays additional indicators R for reply ID for dent 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 912 1 2 SWITCHING ONTHE UNIT P
100. R SEWE SERE SE OK siena adidas Ke EA cavum EEN 8 3 8 5 Aile EA AE OR RE EA EE diaria 84 8 6 cies bL AAPP A 84 Page Date 6 April 2010 8 1 Section 8 E Pilot s Operating Handbook Handling Servicing and Maintenance XTRA EXTRA 300LT Left blank intentionally 8 2 Page Date 6 April 2010 Pilot s Operating Handbook Section 8 EXTRA 300LT XTRA Handling Servicing and Maintenance SECTIONS 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 hours The Airworthiness Authority may require other inspections by the issuance of airworthiness directives applicable to the aircraft engine propeller and components The owner is responsible for compliance with all applicable airworthiness directives and periodical inspections 8 3 PILOT CONDUCTED PREVENTIVEMAINTENANCE Pilots op
101. RE FLIGHT CHECK 1 Checkthat the circuit breaker is set and switch on the aircraft power supply N 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 Aftertheswitch ontesthas elapsed and no error message is written in the display the transponder switches to the mode set on the mode selector A 912 4 Page Date 6 April 2010 Pilot s Operating Handbook Section 912 EXTRA 300LT XTRA BECKER BXP 6401 Transponder NOTE The blind encoder is only powered if the transponder is not switched OFF at least SBY A blind encoder needs a warm up time sometimes a several minutes Therefore although the solid state transponder needs no warm up time turn the transponder to SBY immediately after starting the engine 912 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 912 1 4 SQUAWKSELECTION 1 Thetransponder remains switched inthe standby mode until requested by the ground station A
102. RGE nr 2 8 Structural Temperature Colour Limitation a aaaaaiaaaaaaaass saaasnnnnnannnnsanannnnnasnnnnnanannaanaanana 2 8 MAXIMUM OPERATING ALTITUDE sees esse see naak ea KEER AAR RR ER nnnm nnn nnn nannte nane nnn 2 8 Bnisiuiis il ce c 2 8 MARKINGS AND PLACARDS Rae RAGE EER RA AAR ERGE AR KRAAK RR nna AAR ERGE assa sn nnns asas nnn ee ee 2 8 Aircraft Identification Plate 2 0 ee RR ee AA Re ee AA ee ee ee ee ee ee de ee ee ee ee ee ee nnns 2 8 Operating Placards cn onset Nii ae ne AA N T E 2 9 Instrument Markings ooooocccccccnonoooccccccnnnoonnnccccnnnnn non eene nennen nennen ee ke ee nen ee ke ee sinn 2 14 KINDS OF OPERATION EQUIPMENT LIST sesse sesse een ese eek ER Ee ee ek Raak ee RE ee ARE Re ee RR Rea RR EE ae 2 15 de cl EE N EE EE NEeCeEeEeg 2 16 Page Date 6 November 2012 2 1 Section 2 Pilot s Operating Handbook Limitations XTRA EXTRA 300LT Left blank intentionally 2 2 Page Date 6 April 2010 Pilot s Operating Handbook Section 2 X TRA Limitations EXTRA 300LT 2 1 2 2 2 3 2 4 2 4 1 GENERAL This section includes operating limitations instrument markings and basic placards necessary for the safe operation of the aircraft its engine standard systems and standard equipment The limitations included in this section have been approved by the EASA Observance of these operating limitations is required by national aviation r
103. S 1200 The VFR code for any altitude in the US Refer to ICAO standards elsewhere 7000 The VFR code commonly used in Europe Refer to ICAO standards 0021 The VFR code commonly used in Germany default is set to 0021 at time of installation 7500 Hijack code Aircraft is subject to unlawful interference 7600 Loss of communications 7700 Emergency 7777 Military interceptor operations Never squawk this code 0000 Military use Not enterable Care should be taken not to select the code 7500 and all codes in the 7600 7777 range which trigger special indicators in automated facilities Only the code 7500 will be decoded as the hijack code An aircraft s transponder code if available is utilized to enhance the tracking capabilities of the ATC facility therefore care should be taken when making routine code changes 913 1 3 KEYSFOR 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 913 4 Page Date 6 April 2010 Pilot s Operating Handbook Section 913 EXTRA 300LT XTRA GARMIN GTX 327 Transponder 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 identifi
104. S eL EUN 918 3 918 2 1 Instrumentmarkings ETERNI M 918 3 918 3 EMERGENCY PROCEDURES 4 ranura Ern ner iia 918 4 918 4 NORMAL PROCEDURES iseer Ee ee ae eN eke NR Se ge a 918 4 918 5 dz aei ec HE EE 918 4 918 6 WEIGHT amp CENTER OF GRAVITY skies RENE seek Se ne Ge RAS cian croatas en eiie 918 4 918 7 SYSTEM DESCRIPTION EE 918 5 918 7 1 Instrument Panel Layout RRE 918 6 918 8 HANDLING SERVICING AND MAINTENANCE esse ees ese ee ese ee ee ee Re ee Ge eke ee ee 918 6 Page Date 6 April 2010 918 1 Section 918 Pilot s Operating Handbook EIMVP 50P XTRA EXTRA 300LT Left blank intentionally 918 2 Page Date 6 April 2010 Pilot s Operating Handbook Section 918 EXTRA 300LT XTRA ElMVP 50P 918 1 GENERAL The MVP 50P is a Glass Panel Engine Monitor that provides both analog and digital displays with digits that blink and change colors when yellow or red operating ranges are reached All ofthese features are designed to alert the pilot the moment any monitored function exceeds its normal operating limit The following features are not available in the configuration installed inthe EXTRA 300LT External dimmer potentiometer External warning and caution light Voice alarm System Screen Weight and Balance not applicable do not use Checklists 1 3 not applicable do not use Gear warning and TAS Setup Screen Pressure Altitu
105. S solution will automatically restore once the magnetic vector can again be resolved Within a region approximately 750 nautical miles from the magnetic pole the conditions described above are expected to be persistent 917 7 7 HAZARD AWARENESS EFD1000 PFD PRO AND MFDS ONLY NOTE Maneuvering based solely on the EFD1000 terrain and obstacle display is extremely dangerous and prohibited Pilot in command has the responsibility to see and avoid terrain and other obstacles Page Date 6 November 2012 917 9 Section 917 Pilot s Operating Handbook ASPEN EFD1000 500 System XTRA EXTRA 300LT The EFD1000 500 MFD display ofterrain and obstacle information is advisory only In addition the system does not provide terrain or obstacle alerts Not all obstacles within a given region will be charted The pilot is responsible for terrain and obstacle avoidance by visual means NOTE Maneuvering based solely on the EFD1000 traffic display is not authorized The pilot in command has the responsibility to see and avoid traffic The EFD1000 500 MFD and EFD1000 PFD will display traffic when connected to a TIS source e g Garmin GTX 33 or GTX 330 The TIS information is only available in the US Traffic information is presented to assist the pilot in visually identifying nearby aircraft NOTE The EFD1000 500 moving map display is not a substitute for approved maps or charts required by the operating rules Approved maps and charts m
106. StatLei 0 15 1 60 O 1 Altimeter front United Instr UI5934PD 3 A 134 30416 0 39 0 66 O 1 Altimeter front metric United Instr UI5934PD 3M A 665 33652 0 39 0 66 A 1 Altimeter front km Winter 4 FGH 10 31393 0 60 0 66 A 1 Altimeter front ft Mikrotechna Praha LUN 1128 10B06 34159 0 59 0 65 A 1 Altimeter rear United Instr UI5934PD 3 A 134 30416 0 39 1 62 R 1 Altimeter rear metric United Instr UI5934PD 3M A 665 33652 0 39 1 62 A 1 Altimeter rear km Winter 4 FGH 10 31393 0 60 1 62 A 1 Altimeter front ft Mikrotechna Praha LUN 1128 10B06 34159 0 59 1 61 A 1 Vertical Speed Ind United Instr UI7030 C 27 01485 0 35 1 62 O 1 Vertical Speed Ind metrig United Instr UI7030 M C 194 33653 0 35 1 62 A 1 Vertical Speed Ind metric Winter 5 STVM 15 31564 0 45 1 62 A 1 Vertical Speed Ind fpm Mikrotechna Praha LUN 1144 BOB1 34161 0 40 1 61 A 1 Vertical Speed Ind m s Mikrotechna Praha LUN 1144 F0B1 34162 0 40 1 61 A 1 Attitude Gyro RC Allen RCA2600 2 0 tilt 33027 0 24 1 63 O electronic 2 1 4 1 Attitude Gyro RC Allen RCA2600 2 0 tilt 33881 0 13 1 61 A electronic 2 1 4 102 0202 01 1 Attitude Gyro RC Allen RCA2600 3 0 tilt 33217 0 45 1 63 O electronic 3 1 8 1 Attitude Gyro RC Allen RCA2600 3 0 tilt 33882 0 19 1 61 A electronic 3 1 8 102 0203 01 1 Slip Indicator RC Allen 444 0010 01 33529 0 03 1 63 A on RCA 2600 1 Stall Sensor Extra 7D106 001 V
107. T LO LOO ojejojojo o OISoleIelelSISIEISIEISISISISISOISISID ojejojojo ojo TIN CO SF LO N QO x C co sr to co r o0 O OO t0O O LO O LO O LO LO O LO O LO OO ppp ii iii TIAN OO ST SILO LO GO PM 00 0 ojo OO TIDITISI OIE OD TIN ID EOIOI LO co CN O TIN SERIES OLINA CO C9 TOOL ED OD 1 OO SF O Ol ON SILO mR O TOILET CO LO D O OE TITEL 00 CN CO TPT TPT INI NINN NY NY 09 09 09 09 SF SP SEY LO LO LO CO CO 0000 00 O OD ojojojojo o ejojojojojoiolojoiloioioioi opimboolojiojioioioejiolo jo jojiojyo TIN OO sr LO N ON OT LO OM CO OQ OG Ny CO CO QIN STE OO oN SE CO OO O CN TY TPT TPT TTT TTI NIN NN OOI OO OT TT SE sla LO Sojo FTT TTP TI TI OON NI AINI OON QI 09 090 09 09 09 09 091 09 CO OO sr sE E SE NY CO st LO OLR 00 DIE NCO SILO CO CO D O CN CO SE tO CO CO MD O TIN CO SE LO CO I CO N o SO SF CO NY CO LO OD CO MJ LO MD CO QN COO sr O0 CN CO O Tt O0 DER 7 10 CO TY TIN NEN CO CO SF SF SE LO LO CO CO CO I N 00 CO Od O OD CO Of 7 TINY NY 09 CO CO SF SE LO add mik ld mik lk al dl Dl Dl O ll De al O LO O LO O LO O LO O LO O LOJO LO O LO O LO O LO O LO O LO O LO O LO O LO O LO O LO O LO OINI OINIOINISOINIOINI I SOINI IOINI I OINIOINISINI OINI OINIOINI ISINI OINI OINIOINIQ N ewe Ho Sen Pes eo Pa Ls pa
108. T STROBE NAV LANDING WARNING ES STARTER f gin PUMP Leurs Leurs INSTR PEDALS EUM LIGHT con f e 11 12 13 14 15 16 17 18 19 20 21 22 23 Figure 2 Switches Circuit Breaker 7 6 Page Date 22 April 2015 Pilot s Operating Handbook E Section 7 EXTRAS300LT 2A TRA Description and Operation of Aircraft and Systems Position Item Fig 1 COM G meter Volt Amperemeter Airspeed indicator Magn direction indicator Altimeter Manifold pressure fuel flow Trim position indicator RPM Indicator Transponder Magneto selector switch and starter Oil pressure oil temperature EGT CHT ELT remote switch Trim switch PTT switch Fuel quantity center tank Fuel quantity wing tank Circuit breaker Switches OONOOARWND Position Item Fig 2 Alternator warning light incl press to test feature Battery switch red cap Alternator switch red cap Boost pump switch Strobe lights switch NAV lights switch Avionic switch circuitbreaker Left pedal adjustment switch Right pedal adjustment switch Landing light switch Stall warning circuit breaker spare Starter circuit breaker Alternator field circuit breaker Boost pump circuit breaker Strobe lights circuit breaker NAV lights circuit breaker Instruments circuit breaker Electric pedal adjustment circuit breaker Electric trim system circuit breaker Landing light circuit breaker COM circuit breaker Transponder circuit breaker OO ONOU KOL
109. TC 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 ATC 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 code is stored in each case andis also activated when the transponder is switched on IMPORTANT CODES 1200 The VFR code for any altitude in the US Refer to ICAO standards elsewhere 7000 The VFR code commonly used in Europe Refer to ICAO standards 0021 The VFR code commonly used in Germany default is set to 0021 at time of installation 7500 Hijack code Aircraft is subject to unlawful interference 7600 Loss of communications 7700 Emergency Page Date 6 April 2010 912 5 Section 912 Pilot s Operating Handbook BECKER BXP 6401 Transponder XTRA EXTRA 300LT 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 i
110. TION 5 PERFORMANCE Table of Contents Page GENERAL ees 5 3 Performance OE RE EE EE OR sites 5 3 Definitions Of in OE dx pute eee veneta eue spas e E uu iL n duuteds 5 8 Sample Problemi EE 5 8 ISA CONVERSION ee M 5 5 AIRSPEED CALIBRATION ccccoconsicncsni nnaonnanerganenndnnanidnnnninindd linda amid aeaaea aana ena RR agaaa 5 6 STALE SPEED ec ET EE EE N 5 7 TAKE OFF PERFORMANCE esse eek knee se kke ek Reese ee see ee bee aa andalan RE ke sek Ke Ge AE 5 8 RATE OF CLIMB PERFORMANCE eeuse ses vee ene see ee seek baa KA eg ae rana ma nnnm kd ade Rana Ged aaa 5 10 TIME DISTANCE FUEL TO CLIMB ees esse eene ee see ee sae eke ek Red ne 5 11 RANGE RE EE AE EE EE EE aaa Sae e EARE 5 12 ENDURANCE EE DE EE RE aaa 5 13 CRUISE SPEEDS 5 14 CRUISE PERFORMANCE eerste see ees nee siese base ees sie ek gegee gede es ede ee se ask ede ke Ed ek ged EED ele 5 15 TIME DISTANCE FUEL TO DESCENT ees sesse sees ees soe eke ee ese ee gee eke ee ke ee Ge eke ek nnns 5 16 LANDING PERFORMANCE 11221 22222225222 ees ese REG wee Ge bk ae ond Ee ak an EES 5 17 Page Date 6 April 2010 5 1 Section 5 Pilot s Operating Handbook Performance XTRA EXTRA 300LT Left blank intentionally 5 2 Page Date 6 April 2010 Pilot s Operating Handbook Section 5 XTRA Performance
111. The MENU key displays a context sensitive list of options This options list allows you to access additional features or make settings changes which relate to the currently displayed page The clear key CLR is used to erase information or cancel an entry Press and hold this key to immediately display the Default Navigation Page regardless of which page is currently displayed Theenterkey ENT is used to approve an operation or complete data entry Itis also used to confirm information such as during power on Thelargerightknobis used to select between the various page groups NAV WPT AUX or NRST With the on screen cursor enabled the large right knob allows you to move the cursor about the page The small right knob CRSR is used to select between the various pages within one of the groups listed above Press this knob momentarily to display the on screen cursor The cursor allows you to enter data and or make a selection from a list of options BOTTOM ROW KEYS The nearest NRST key displays the nearest airports page Then turning the small right knob steps through the NRST pages The OBS key is used to select manual or automatic sequencing of waypoints Pressing the OBS key selects OBS mode which will retain the current active to waypoint as your navigation reference even after passing the waypoint i e prevents sequencing to the nextwaypoint Pressing the OBS key again will return to normal operation with automatic se
112. Then let starter cool for 30 minutes EMERGENCY PROCEDURES Not affected NORMAL PROCEDURES The following starting procedures are recommended however the starting conditions may necessitate some variation from these procedures 1 Perform Pre flight inspection 2 Setpropeller governor control to High RPM position 3 4 5 Open throttle approximately 1 4 travel Battery switch OFF Alternator switch OFF N CAUTION Risk of damage of electrical system due to reversion of polarity Check correct polarity before connecting the power plug to the receptacle 6 Put the external power plug into the board receptacle 7 Check engine indicating to be operative 8 9 Move mixture controlto FULL RICH until a slight but steady fuel flow is noted approximately Turn boost pump ON 3 to 5 seconds and return mixture control to IDLE CUT OFF 10 Turn boost pump OFF Page Date 6 April 2010 905 3 Section 905 Pilot s Operating Handbook External Power XTRA EXTRA 300LT N 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 Move mixture control slowly and smoothly to FULL RICH 12 Check the oil pressure gauge If minimum oil pressure is not indicated within 30 seconds shut off the engine and determine trouble 13 Ba
113. aa une s 1 7 Page Date 6 April 2010 1 1 Section 1 Pilot s Operating Handbook General XTRA EXTRA 300LT Left blank intentionally 129 Page Date 6 April 2010 Pilot s Operating Handbook Section 1 EXTRA 300LT XTRA General 1 0 1 1 1 2 1 3 1 3 1 DESCRIPTION The fuselage of the EXTRA 300LT is built of a tig welded steel tube construction Wings empennage and landing gear are manufactured from composite material The aircraft is a two seater with the rear seat instrumented for pilot in command SPECIFICATION OF CLASS The aircraft is certified in normal and acrobatic category MANUFACTURER EXTRA Flugzeugproduktions und Vertriebs GmbH Flugplatz Dinslaken 46569 H nxe Federal Republic of Germany TECHNICAL DATA 3 VIEW DRAWING Page Date 6 April 2010 1 3 Section 1 General XTRA Pilot s Operating Handbook EXTRA 300LT 1 3 2 MAINDATA Length Height Span Wheel base Wheel track 1 3 3 WING Wing span Wing area Airfoil Chord MAC Aileron area Aileron deflection 1 3 4 HORIZONTALTAIL Span Area Airfoil 1 3 5 ELEVATOR Area Elevator deflection Trim tab deflection 1 3 6 VERTICAL TAIL Area Airfoil 1 3 7 RUDDER Area Rudder deflection 7 01 m 23 00 ft 2 62 m 8 60 ft 8 00 m 26 25 ft 5 07 m 16 63 ft 1 80 m 5 91 ft 8 0 m
114. based on the last valid GPS position then estimated by Dead Reckoning methods All information normally derived from GPS will become less accurate over time SEARCHING A NEARBY AIRPORT To select a nearby airport as a direct to waypoint Press the Direct To key on the right side of the unit 2 Touch the NRST APT tab in the Direct To window The nearest 25 airports within 200NM will be listed The airport at the top of the list is the nearest airport To review the other nearest airports touch the Up and Down keys to scroll through the list 3 Touch the desired airport to select it The selected airport will be displayed in the Waypoint page 4 Touch the Activate key or press the small right knob to activate the selection 5 The Map page will now be displayed with the new Direct To course 9224 NORMAL PROCEDURES TO ACTIVATE AN EXISTING FLIGHT PLAN 1 Press the Direct To key on the right side of the unit 2 Touch the FPL tab in the Direct To window 3 Touch the flight plan waypoint you want to navigate directly to The Direct To Waypoint page will display information about the selected flight plan waypoint 4 Touch the Activate key or press the small right knob to activate the selection 5 The Map page will now be displayed with the new Direct To course 9225 PERFORMANCE Not affected Page Date 6 November 2012 922 7 Section 922 Pilot s Operating Handbook GARMIN GTN 635 650 750 XTRA EXTRA 300
115. blinking on the MVP 50P display press any button while viewing the Main Engine Screen To determine the current operating band for a function refer to the pointer position in the color band or the color of the digits NOTE Any instrument can fail at any time Acquire proper training to safely operate this aircraft withoutthe use of this instrument Refer to the Operating Instructions for further operating and safety information Page Date 6 April 2010 918 5 Section 918 2 Pilot s Operating Handbook EIMVP 50P XTRA EXTRA 300LT 918 7 1 INSTRUMENTPANELLAYOUT Generally an alternate panelis used to carry the MVP 50 Forthat reasonthe circuit breaker layout also changes as shown in Figure 2 2 3 amp 6 gt Le rr ov v i p ETHER O G G i o MT STALL 000 mai A eee M e O A ECT 66 CHT 66 VOLTS bv EN DIFF Oe DIFF le dng 1 2 ESA ml IO oo ES EN 50006 E j 8 9 10 1 12 13 14 15 Figure 2 Alternate Panel Layout Position Item Fig 2 Alternator warning light incl press to test feature located in the switch row if sub panel is not used Alternator field circuit breaker Boost pump circuit breaker Strobe light circuit breaker NAV light circuit breaker Electrical pedal adjustment circuit breaker Landing light circuit breaker Stall warning circuit breaker MVP 50 circuit breaker Electrical trim system circuit
116. book Electric Pedal Adjustment XTRA EXTRA 300LT Left blank intentionally 902 2 Page Date 6 April 2010 Pilot s Operating Handbook Section 902 EXTRA 300LT X TRA Electric Pedal Adjustment 902 902 1 902 2 902 3 902 4 902 5 902 6 ELECTRIC PEDAL ADJUSTMENT GENERAL To improve seat and control convenience the EXTRA 300LT is equipped with an electric pedal adjustment system The pedal adjustment system provides an in flight capability to adjust the pedals according the pilots size and operation For example a more relaxed stretched seating position for long cross country flights is possible LIMITATIONS An adjustment of the pedal position during takeoff and landing is not allowed It is recommended not to adjust the pedals when radio transmissions are made or when the magnetic direction indicator is used EMERGENCY PROCEDURES Pedal Run away Pedal switch USE in reverse direction of run away if no effect PEDALS Circuit Breaker PULL NORMAL PROCEDURES Onground Rudder pedals ADJUST position using the pedal switches CHECK full control inputs rudder and aileron CHECK full rudder deflection while braking In flight Rudder pedals ADJUST position using the pedal switches CHECK heels reach the pedal swivel axes and aileron control rods are free PERFORMANCE Not affected WEIGHT AND BALANCE Not affected Page Date 6 April 2010 902 3 ar sel Adjustment X TRA Pilot s Ope
117. bstructions in the pitot system that might occur However post landing the monitor remains active and as the airplane slows below 30 KIAS the system will posta red X in place ofthe attitude and heading information and postthe CHECK PITOT HEAT message In this circumstance restoring the GPS system or cycling power to the affected EFD1000 will restore normal monitor operation In some acrobatic maneuvers it may be possible to activate the Pitot Obstruction Monitor for example at indicated airspeeds below 30 KIAS Under these circumstances if the groundspeed exceeds 50kts the monitor will activate To restore normal ADAHRS operation increase the indicated airspeed to a value greater than 30 KIAS the affected display will then perform an automatic reset 917 7 3 DATABASES EFD1000 500 MFD ONLY NOTE To operate the EFD1000 MFD and EFD500 MFD the database currency date must be acknowledged prior to each flight Flight with an expired database is not recommended An expired database does not prevent terrain or other Nav Map features from being displayed on the MFD Each EFD1000 500 MFD uses several databases The EFD1000 PFD does not require a database The Jeppesen NavData Cultural database and Obstacle database are all combined into a single download from Jeppesen Terrain data is loaded at the factory and does not require periodic updating Data base valid dates are displayed at power up and require a pilot action to acknowledge Databa
118. by frequency in blue is active for editing Turn the large right knob to select the desired megahertz MHz value Turnthe small right knob to select the desired kilohertz kHz value Press the small right knob to transfer the standby frequency to the active window USING TOUCHSCREEN Touch the Standby window A pull down keypad will appear with the current Standby frequency highlighted Touch the numeric keys to add the desired values and touch Enter to accept the displayed value and place it into the Standby window Touching the XFER key will place the selected frequency directly in the Active window Touch the Active top frequency window to flip flop the Active and Standby frequencies Page Date 6 November 2012 922 9 Section 922 GARMIN GTN 635 650 750 XTRA Pilots Operating Handbook EXTRA 300LT Active Transponder Selection 4 com con 133 90 Intercom Active Transponder Audio MIC XPDR NAV Panel 1 IDENT 117 95 MON STRY o 115 ER Backspace Altitude Reporting ENR Demo OPSIT Pon Code Pzh Enter P Transponder Mode Keys Figure 4 GTN 750 XPDR Operation 922 7 4 REMOTETRANSPONDER OPERATION Transponder Control Code Key Code Display and Mode Reply Annunciation Squawk Code Backspace Key VFR Squawk Code 1200 Key Squawk Code Window Numeric Keypad Green Bar Indicates Active Condition Enter Key Context Sensitive Instructions for Rotary Knob Op
119. cation 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 CLR Resets the Count Up and Count Down timers and cancels the previous keypress during code selection 8 Reduces Contrast and Display Brightness when the respective pages are displayed Also enters the number eight into the Count Down timer 9 Increases Contrast and Display Brightness when the respective pages are displayed Also enters the number nine into the Count Down timer FUNC Changes the page shown on the right side of the display Displayed data includes Pressure Altitude Flight Time Count Up timer Count Down timer and may include Contrast and Display Brightness depending on configuration refer to the screen description below SCREEN DESCRIPTION PRESSURE ALT Displays the altitude data supplied to GTX 327 in feet hundreds of feets i e flight level or meters depending on configuration FLIGHT TIME Displays the Flight Time which is controlled by the START STOP key COUNT UP TIMER Controlled by the START STOP and CLR keys COUNT DOWN TIMER 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
120. crobatics the GPS signal can get lost 1 Reset switch OFF and ON the unit to regain the GPS signal SEARCHING A NEARBY AIRPORT To select a nearby airport as a direct to waypoint 1 Press the direct to key The select direct to waypoint page will appear with the waypoint identifierfield highlighted 2 Turn the large right knob to highlight the nearest airport NRST field 916 4 Page Date 6 April 2010 Pilot s Operating Handbook Section 916 EXTRA 300LT XTRA GARMIN GNC 420W GNS 430W 916 4 916 5 916 6 916 7 916 7 1 3 Turn the small right knob to display a window showing up to nine nearby airports 4 Continue turning the small right knob to scroll through the list and highlight the desired airport 5 Press ENT to confirm the selected airport and ENT to activate the direct to function NORMAL PROCEDURES TO ACTIVATE AN EXISTING FLIGHT PLAN 1 Press FPL and turn the small right knob to display the flight plan catalog 2 Press the small right knob to activate the cursor 3 Turn the large right knob to highlight the desired flight plan and press MENU to display the flight plan catalog options 4 Turn the large right knob to highlight Activate Flight Plan and press ENT 5 Press and hold the CLR key to open the default NAV page PERFORMANCE Not affected WEIGHT amp CENTER OF GRAVITY Refer to the equipment list in Section 6 of this Handbook SYSTEMDESCRIPTION KEY ANDKNO
121. ction and Count Down entry Returns cursorto 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 ofthe altitude indicates that the airplane is climbing or descending Page Date 6 April 2010 915 5 Section 915 Pilot s Operating Handbook GARMIN GTX 330 Transponder XTRA EXTRA 300LT 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 timer is controlled by the START STOP and CLR keys Pressing the CLR key zeros the display COUNT DOWN TIMER The count down timer is controlled by START STOP CLR and CRSR keys The initial Count Down timeis entered with the 0 9 key
122. d line 2700 rpm G METER green arc 59 89 yellow arc 89 10g red line 109 FUEL FLOWINDICATOR greenarc 0 gal h 35 gal h red radial 35 gal h 2 14 Page Date 6 April 2010 Pilot s Operating Handbook Section 2 EXTRA 300LT XTRA Limitations MANIFOLD PRESSURE INDICATOR greenrange 10 Hg 30 Hg 2 15 KINDS OF OPERATION EQUIPMENT LIST The aircraft may be operated in day VFR when the appropriate equipment is installed and operable No Pilot s Operating Handbook Supplement grants approval for IFR operation Flight in icing conditions is prohibited The following equipment list identifies the systems and equipment upon which type certification for each kind of operation was predicated The following systems and items of equipment must be installed and operable for the particular kind of operation indicated NORMAL ACROBATIC 1 seat 2 seats COMMUNICATION 1 Transceiver VHF 1 1 1 ELECTRICAL POWER 1 Battery 1 1 1 2 Alternator 1 1 1 3 Ammeter 1 1 1 4 Voltmeter 1 1 1 FLIGHTCONTROL SYSTEM 1 Elevator trim control electric 1 1 1 2 Stall warning 1 1 1 FUEL 1 Boost pump 1 1 1 2 Fuel quantity indicator wing tank 1 1 1 3 Fuel quantity indicator center tank 1 1 1 5 Fuel flow indicator 1 1 1 6 Fuel pressure indicator 0 0 0 LIGHT 1 Wing tip NAV lights 0 0 0 1 Wing tip strobe lights 1 1 1 NAVIGATION 1 Altimeter 1 1 1 2 Airspeed indicator 1 1 1 3 Mag direction indicator 1 1 1 4 OAT i
123. de Calibration Screen Flaps Trim and Special Function Calibration Screen Calibrating Airspeed Gear Position and Unsafe Indicators Gear Warning An additional fuel contents transmitter is installed in the RH wing when the MVP 50P is used This supplementis written for Software Version 2 7 andis not suitable for earlier software versions This software version corresponds to the MVP 50P Operating Instructions Doc OI 1002051 Revision D 4 25 08 Some differences in operation may be observed when comparing the information in this supplementto later software versions Verify the information herein with the MVP 50P Operating Instructions you received with your unit There you find also further information 918 2 LIMITATIONS 918 2 1 INSTRUMENTMARKINGS The following markings deviate from the values given in Section 2 of this Handbook RPMINDICATOR greenrange 2000 rpm 2700 rpm redline 2700 rpm FUEL PRESSURE INDICATOR greenrange Opsig 14 psig redline 14 psig Page Date 6 April 2010 918 3 Section 918 Pilot s Operating Handbook EIMVP 50P XTRA EXTRA 300LT 918 3 EMERGENCY PROCEDURES Not affected 918 4 NORMAL PROCEDURES Magneto Check Checkthe magnetos at 1800 RPM Allowed drop is 175 RPM max difference 50 RPM Check Alternator Output Move also the propeller control through its complete range to check operation and return to full HIGH RPM position Turn boost pump ON check indicato
124. de 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 Two user specific VFR codes can be stored and activated on the transponder Page Date 6 April 2010 911 5 Section 911 Pilot s Operating Handbook BECKER ATC 4401 Transponder XTRA EXTRA 300LT 4 Storing a new VFR code Set the code to be stored in accordance with section B Press store push button STO J the set code then flashes Press the VERT push button F or the VFR2 push button G wit hin 3 seconds to store the code under the corresponding button If neither button F or G is pressed within 3 seconds the flashing stops and the s
125. e and operate the rudder through a cable system Springs keep the cables under tension when they are not operated 7 5 5 SECONDARY CONTROL The elevator trim tab is actuated by an electric trim servo located in the right rear fuselage It is controlled by a trim switch integrated in the control stick handle Trim position is indicated by a LED indicator on the instrument panel The canopy lock is operated from the outside by a handle on left side of the canopy by reaching into the cockpit through the window Inside a handle is located in both cockpits used for locking as well as for normal operation and for emergency release The starter magneto switch is located on the right side of the instrument panel in front of the rear seat 7 6 INSTRUMENTATION The Extra 300LT is equipped with flight instruments in both cockpits Instruments and placards can be provided with markings in either metric or English units The colour markings in instruments follow US FAR part 23 recommendation see section 2 Page Date 6 April 2010 7 5 Section 7 Pilot s Operating Handbook Description and Operation of Aircraft and Systems X TRA EXTRA 300LT 7 6 1 INSTRUMENT PANEL REAR COCKPIT Control Stick 1 2 3 4 5 6 7 8 9 10 ON ETE ON ON I ON ON CT ENE EET C C 40 CD WD V WY K RD H U Ao ARI OFF n CO 10 0 5 10 5 m Di t O O STALL ALT BOOS
126. e 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 stringertube 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 6 April 2010 Pilot s Operating Handbook X TRA EXTRA 300LT Section 9 901 902 903 904 905 906 907 908 909 910 911 912 913 914 915 916 917 918 919 920 921 922 LI LI BL E id od Tey E dd E E Et P EL EI Ed P EE E SECTION9 SUPPLEMENTS SUPPLEMENTS Doc No EA 0D701 1 Table of Contents Pages III eat 4 p Steerable Tail Wheel uie Ke EN EER ERGE KEER ENE ER EE EA sene ae ee Ee de naim AR Ge de Ee De Ge na 4 p Electric Pedal Adjustment esse EER EER RR EE ER KERR RE EER KERR RE EE EE ER KERR RE EER EER KERR RE nnns 4 p Cabin Heating System E 4 p Accelerometer TL 3424 EXT 2a222aaaaaazaaaaaaannnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnann n nnn EE Gee ee 6 p External Po Wei 4 p Digital RPM Wi H TE 6 p SMOKE Systeri e OE a Rua 8 p Single Seat Canopy SR EE RR EE N 4 p iS dr
127. e for edition of revisions amendments and supplements Amendments which affect the airworthiness of the aircraft will be announced in the mandatory Service Bulletins issued by the manufacturer EXTRA Flugzeugproduktions und Vertriebs GmbH coming along with the Airworthiness Directive AD publication issued by the EASA The owner is responsible for incorporating prescribed amendments and should make notes about these on the records of amendments Should this Flight Manual get lost inform EXTRA Flugzeugproduktions und Vertriebs GimbH Flugplatz Dinslaken 46569 H nxe Federal Republic of Germany Should this Flight Manual be found kindly forward it to the civil board of aviation in the country the aircraft is registered Page Date 6 April 2010 S EXTRA WARNINGS CAUTIONS AND NOTES The following definitions apply to Warnings Cautions and Notes W NXN gt Operating procedures techniques etc which could result in personal injury or loss of life if not carefully followed N CAUTION gt Operating procedures techniques etc which could result in damage to equipment if not carefully followed NOTE z An operating procedures technique etc which is considered essential to emphasize Shall Will Should and May The words Shall or will is used to express a mandatory requirement The word should is used to express nonmandatory provisions The word may is used to express permissib
128. e 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 brighiness and in the Configuration Mode IMPORTANT CODES 1200 The VFR code for any altitude in the US Refer to ICAO standards elsewhere 7000 The VFR code commonly used in Europe Refer to ICAO standards 7500 Hijack code Aircraft is subject to unlawful interference 7600 Loss of communications 7700 Emergency 7777 Military interceptor operations Never squawk this code 0000 Military use Not enterable 915 4 Page Date 6 April 2010 Pilot s Operating Handbook Section 915 EXTRA 300LT XTRA GARMIN GTX 330 Transponder Avoid selecting code 7500 and all codes in the 7600 7777 range These trigger special indicators
129. e of Go Around RPM conirol must be set to max RPM before applying power 4 8 3 BEFORELANDING 1 Landing approach PROCEED 2 Airspeed on final maintain 85 KIAS 157 km h 3 Elevator trim ADJUST 4 8 Page Date 6 April 2010 Pilot s Operating Handbook Section 4 XTRA Normal Procedures EXTRA 300LT 4 8 4 4 9 4 10 4 11 NOTE Stall speed will be MTOW 820 kg 1808 Ibs 60 KIAS 111 km h MTOW 870 kg 1918 Ibs 62 KIAS 115 km h MTOW 950 kg 2095 Ibs 65 KIAS 120 km h NORMALLANDING 1 Landing PERFORM as practicable with respect to surface and weather condition 2 Landing light As desired NOTE The rudder is effective down to 30 KIAS 56 km h 3 Touchdown 3 point landing 4 Throttle CLOSE IDLE 5 Braking Minimum required GO AROUND Decide early in the approach if itis 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 110 KIAS 204 km h rotate to go around altitude SHUTDOWN 1 Boost pump OFF 2 Landinglight OFF 3 Engine RUN for 1 min at 1000 RPM 4 Dead cut check PERFORM 5 Avionic switch OFF 6 Mixture IDLECUT OFF 7 Ignition switch OFF 8 Battery switch OFF LEAVING THE AIRCRAFT 1 Canopy CLOSE and LOCK 2 Baggage compartment CLOSE and LOCK 3 Aircraft SECURE 4 Pitotcover ATTACH 5 Log book COMPLETE
130. e required Refer to local regulations 924 6 Page Date 22 April 2015 Pilot s Operating Handbook Section 924 EXTRA 300LT XTRA KANNAD AF 406 ELT 924 8 2 BATTERY REPLACEMENT Carried out by an accredited PART 145 or FAR 145 or equivalent maintenance station BATTERY REPLACEMENT REQUIREMENTS Battery replacement is mandatory after more than 1 hour of real transmission cumulated duration beforeoronthe battery expiration date afterusein an emergency afteraninadvertantactivation of unknown duration Only an original and approved battery pack included in battery KIT BAT200 P N S1840510 01 supplied by KANNAD must be installed SAFT FRIWO Lithium Manganese Dioxide 2 x M20 D type cells KANNAD refuses all responsibility and invalidates all warranty should other packs be installed Battery packs or KITs are available from any KANNAD distributor or dealer A list of distributors is available on http www kannad com Page Date 22 April 2015 924 7 Section 924 Pilot s Operating Handbook KANNAD AF 406 ELT XTRA EXTRA 300LT Left blank intentionally 924 8 Page Date 22 April 2015
131. e the front partition of the baggage compartment preferential To securethe baggage Loosen the tie down straps by means of the cam buckles 9 Position baggage below the tie down straps Tighten the tie down straps by means of the cam buckles 9 Position baggage net overthe baggage Clip the baggage net hooks into the eye bolts 8 10 o POND 7 15 LANDINGLIGHT To improve visibility during landing approach a landing light is integrated in the RH lower cowling The landing light is controlled by the LANDING LIGHT switch on the right instrument panel The system is protected by the LANDING LIGHT circuit breaker 7 14 Page Date 6 April 2010 Pilot s Operating Handbook Section 7 EXTRA 300LT 2A TRA Description and Operation of Aircraft and Systems Figure 5 Baggage Compartment Page Date 6 April 2010 7 15 Section 7 Pilot s Operating Handbook Description and Operation of Aircraft and Systems X TRA EXTRA 300LT Left blank intentionally 7 16 Page Date 6 April 2010 ii M EXTRA SECTION 8 HANDLING SERVICING amp MAINTENANCE TABLE OF CONTENTS Paragraph Page 8 1 INTRODUCTION me ER EE A 8 3 8 2 AIRPLANE INSPECTION PERIODS sees sesse ees ese ee gee eke eek Ee ee gee eke ek Ee nnn Gee snnt nn nnn 8 3 8 3 PILOT CONDUCTED PREVENTIVE MAINTENANCE esse esse sesse ee ae ee eed ee ee NEEN ee ee 8 3 84 ALTERATIONS OR REPAIR 2 nter nca E
132. eat HANDLING SERVICE AND MAINTENANCE Not affected Page Date 6 April 2010 Section 908 Pilot s Operating Handbook Single Seat Canopy XTRA EXTRA 300LT Left blank intentionally 908 4 Page Date 6 April 2010 Pilot s Operating Handbook X TRA EXTRA 300LT SECTION 909 ARTEX ME 406 ELT Table of Contents Paragraph Page 909 1 GENERAL 909 3 909 2 EIMITATIJ NS s CD EN 909 3 909 3 EMERGENCY PROCEDURES 2 as ent tp nca ees idu eaa nni aan anu ak din see bee kW EE RE ee Rak dua 909 4 909 4 NORMAL PROCEDURES orta Bee Ese nite ERGE aie aoa canine naar nua Sek nde nailon See we Rees ei 909 4 909 5 ddzeli lel MR ME ese ssueaccsetvastsduceasecunvuaseecedasencaurs E 909 4 909 6 WEIGHT amp CENTER OF GRAVITY ouens sae ees Beek Re ERG Ge ER Rek nenne KROG Rek sana natn menn 909 4 909 7 SYSTEM DESCRIPTION e 909 5 909 7 1 SWITCH Operation E 909 5 909 7 2 Sel Test ee 909 5 909 8 HANDLING SERVICING AND MAINTENANCE ees se ees ee ese ee ese ee ee ee Re rra 909 6 909 8 1 Rare EE OE 909 6 909 8 2 SIMI L O 909 6 Page Date 6 April 2010 909 1 Section 909 Pilot s Operating Handbook ARTEXME 406 ELT XTRA EXTRA 300LT Left blank intentionally 909 2 Page Date 6 April 2010 Pilot s Operating Handbook Section 9
133. ee ee ee bee ee see ee see 908 3 Page Date 6 April 2010 Section 908 Pilot s Operating Handbook Single Seat Canopy XTRA EXTRA 300LT Left blank intentionally 908 2 Page Date 6 April 2010 Pilot s Operating Handbook Section 908 EXTRA 300LT XTRA Single Seat Canopy 908 908 1 908 2 908 3 908 4 908 5 908 6 908 7 908 8 SINGLESEAT CANOPY GENERAL For airshow performances the standard canopy can be replaced by a single seat canopy which gives a gorgeous appearance LIMITATIONS With the single seat canopy installed the aircraft is limited to the categories NORMAL and ACRO In the NORMAL category the aircraft can be flown only with the pilot in the rear seat EMERGENCY PROCEDURES Not affected NORMAL PROCEDURES Befor starting engine check front seat area and ensure seat belts and shoulder harness of front seat are completely removed or fastened and secured so that nothing can obstruct the free movementof controls PERFORMANCE Not affected WEIGHT AND BALANCE AND EQUIPMENT LIST Refer to the equipment list in section 6 DESCRIPTION OF THE SYSTEM The single seat canopy has been designed to easily replace the standard canopy This can be achieved by using the same canopy frame hinges and latches included The front seat is covered by the flat portion of the frame in front of the canopy Operation of the locking mechanism is feasible only from the rear s
134. ee nee ane FR be de ei ae RE ERK SE ee Ed EE 905 3 905 5 PERFORMANCE ee EET 905 4 905 6 WEIGHT AND BALANCE esse ses ese ee eg weeg kase an pma kin mni anao ma cna Ak sees ae jaa 905 4 905 7 DESCRIPTION OF THE SYSTEM see ese ee see sesse eke ee ese ee gee eke nennen nnne tnnt sten nn nnn nennt 905 4 905 8 HANDLING SERVICING AND MAINTENANCE eese nnne 905 4 Page Date 6 April 2010 905 1 Section 905 Pilot s Operating Handbook External Power XTRA EXTRA 300LT Left blank intentionally 905 2 Page Date 6 April 2010 Pilot s Operating Handbook Section 905 EXTRA 300LT XTRA External Power 905 905 1 905 2 905 3 905 4 EXTERNAL POWER GENERAL The EXTRA 300LT can be equipped with an external power receptacle system This system provides the capability to start the engine independent of the board battery and further allows feeding the electrical system for longer periods LIMITATIONS The operation limitations are not affected due to the installation of the external power receptacle system For the location of the external power receptacle and protection of the electrical connection cable against overheating the following placard has to be attached on the rear instrument panel with an indicator arrow to the receptacle EXTERNAL POWER 12V DO NOT CRANK FOR MORE THAN 10 SECONDS Allow 20 seconds to cool down between attempts Repeat up to 6 times
135. een yellow and red LEDs These LEDs are located on the upper right corner of the indicator face 2700 3500 Page Date 6 April 2010 Section 906 Pilot s Operating Handbook Digital RPM Indicator XTRA EXTRA 300LT Magneto Control RPMrange RPM restriction Operation placard Press and hold Operation placard Press and release MAGNETO CHECK Three small LED magneto system alert indicator lights are located within the Status aera on the upper left corner of the indicator face The left and right red LED alert indicator lights when illuminated indicate because of loss of ignition signal to the tachometer a possible malfunction of the respective left or right magneto ignition system While performing a magneto check during engine run up the red alert indicator lights will illuminate thus identifying the grounding of the respective right or left magneto systems Ignition Switch Tachometer Magneto Alert Indicator Lights Position LEFT Status LED RIGHT Status LED OFF ON ON RIGHT ON LEFT BOTH Between the left and right magneto ignition system alert indicators is a yellow rpm Synchronization indicator This small yellow indicator is illuminated when there is a difference of more than 50 rpm between the right and left tachometers This indicator also may flicker during extreme rpm excursions of the engine 906 4 Page Date 6 April 20
136. egulations NOTE In case of an aircraft equipped with specific options additional information required for safe operation will be contained in Section 9 Supplements Instrument markings and placards are provided for the acrobatic category only for normal category refer to corresponding limitations This aircraft is certified under Type Certification Data Sheet T C D S EASA A 362 Any exceedance of given limitations has to be reported by the pilot so that necessary inspection or maintenance procedures according to the MAINTENANCE MANUAL EA 300LT can be performed AIR SPEED IAS Never Exceed Speed Vue 221knots 409km h Max Structural Cruising Speed Normal Cat Vue 143knots 265km h Max Structural Cruising Speed Acro Cat I Il HI Vue 160knots 296km h Maneuver Speed Normal Cat Va 143knots 265km h Maneuver Speed Acro Cat I Il III V 160knots 296km h CROSS WIND COMPONENT Max demonstrated cross wind component for take off and landing is 15 knots 27 km h ENGINE Engine type Textron Lycoming AEIO 580 B1A Rated maximum power 235 kW 315 HP 2700 rpm FUEL Minimum grade aviation gasoline 100 1 00LL for alternate fuelgrades see latest revision of Lycoming S l No 1070 Total fuel capacity 221L 58 4US gal Usable fuel capacity 209L 55 2US gal Total fuel capacity for acrobatic in acro amp center tank 69L 18 2US gal Usable fuel capacity for acrobatic in acro amp center tank 67L
137. elch On Off Audio Panel Xpdr Panel and NAV ID On Off Controls Controls HOME Key Photo Sensor SD Card Home Display Function Keys Direct To Key Large and Locking Small Knobs Screw Annunciations Figure 2 GTN 750 Display Layout The system must utilize main software version 2 00 GPS software version 4 0 COM software version 2 01 and NAV software version 6 01 or later EASA FAA approved versions Valid and compatible databases must be installed and contain current data The navigation data incl for final approach segments provided by the GTN series e g moving map amp CDI depiction is for situational awareness only and should not be relied upon for navigation Do not use SafeTaxi or ChartView functions as the basis for ground maneuvering SafeTaxi and ChartView are to be usedfor the pilotto orient himself onthe airport surface to improve situational awareness during ground operation 922 4 Page Date 6 November 2012 Pilot s Operating Handbook Section 922 EXTRA 300LT XTRA GARMIN GTN 635 650 750 922 2 1 PLACARDS GARMIN GPS limited to VFR use only In close proximity to the GTN unit in clear view of the pilot GPS Next to the GTN unit GPS circuit breaker Next to the GMA 35 Remote Audio Panel circuit breaker if installed 922 2 2 SDCARD Proper function of any of the units is predicated on the SD card being present 922 2 3 TERRAIN Terrain proximity and obstacle informat
138. erating the airplane should refer to the regulations of the country of certification for information of preventive maintenance that may be performed by pilots All other maintenance required on the airplane is to be accomplished by appropriately licensed personnel Airplane dealer should be contacted for further information Preventive maintenance should be accomplished with the appropriate service manual 8 4 ALTERATIONS OR REPAIR Alterations or repairs of the airplane must be accomplished by licensed personel Page Date 6 April 2010 8 3 Section 8 E Pilot s Operating Handbook Handling Servicing and Maintenance XTRA EXTRA 300LT 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 Description and Operation 8 6 GROUNDHANDLING 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 eye bolts are provided which can be screwed in the underside of the wing tips If a sighting device is installed a ring plate on the aft attachment point is integrated for that purpose The tail wheel leg can be used as third point to tie down the airplane If the aircraft is parked in the open it must be protected against the effects of weather the degree of protection depending on severity of the weather conditions and th
139. eters contact an authorized Garmin Aviation Service Center 914 1 6 ALTITUDE TRENDINDICATOR When the PRESSURE ALT page is displayed an arrow may be displayed to the right of the altitude indicating thatthe altitude is increasing or decreasing One of two sizes of arrows may be displayed depending on the vertical speed rate The sensitivity of these arrows is set by an authorized Garmin Aviation Service Center 914 1 7 FAILUREANNUNCIATION If the unit detects an internal failure the screen displays FAIL When FAIL is annunciated no transponder data is transmitted 914 6 Page Date 6 April 2010 Pilot s Operating Handbook 2 Section 914 EXTRA 300LT XTRA GARMIN GTX 328 Transponder 914 2 LIMITATIONS Notapplicable 914 3 EMERGENCY PROCEDURES 914 3 1 IMPORTANTCODES 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 9144 NORMALPROCEDURES Notapplicable 9145 PERFORMANCE Notapplicable Page Date 6 April 2010 914 7 Section 914 Pilot s Operating Handbook GARMIN GTX 328 Transponder XTRA EXTRA 300LT Left blank intentionally 914 8 Page Date 6 April 2010 Pilot s Operating Handbook X TR A EXTRA 300LT Paragraph 915 1 915 1 1 915 1 2 915 1 3 915 1 4 915 1 5 915
140. f 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 whilstthe 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 912 1 5 SQUAWKIDENT 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 912 1 6 SELFTESTS OF THE UNIT BITS The following different tests are integrated in the transponder or canbe triggered at the transponder 1 The BIT 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 of the second pushed button The IBIT works as follows in all modes The test 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
141. 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 Page Date 6 April 2010 Pilot s Operating Handbook Section 911 XTRA BECKER ATC 4401 Transponder EXTRA 300LT 3 Afterthe 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 Ablind 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 911 1 3 SQUAWKSELECTION 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 O to 7 can then be set using switch C NOTES If switch B is turned clockwise or counter clockwise the cursor is moved one position to the right or the left The cursor appears only in the code display and is indicated by the flashing digit If no cursor is visible the first digit flashes after a clockwise rotation and the last digit after a counter clockwise rotation When the co
142. from SBY mode only To get into configuration mode press button SEL G turn rotary encoder B until CFG appears in the bottom row ofthe display Refer to BECKER s Pilot s Guide for available options 912 2 LIMITATIONS Not applicable 912 3 EMERGENCY PROCEDURES 912 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 912 4 NORMAL PROCEDURES Not applicable 912 5 PERFORMANCE Not applicable 912 10 Page Date 6 April 2010 Pilot s Operating Handbook X TR A EXTRA 300LT Paragraph 913 1 913 1 1 913 1 2 913 1 3 913 2 913 3 913 3 1 913 4 913 5 SECTION 913 GARMIN GTX 327 TRANSPONDER Table of Contents Page cd dil MEER EE HE IE N AR ER EE M HQ 913 3 Mode Selection Keys tete ete lt ee Ee edd HERR Ge ee eu 913 3 eel AREA RE EL OE EE OR 913 4 Keys for other GTX327 FuncUONS sies seges e Edge ee Deer De et oe dese Seege ed 913 4 LIMITATIONS ii E e id 913 6 EMERGENCY PROCEDURES eege ee EENEG 913 6 important CodeS c M es 913 6 NORMAL PROCEDURES 2 sels Gie eek gee a 913 6 PERFORMANGE EE EE N N N 913 6 Page Date 6 April 2010 913 1 Section 913 Pilot s Operating Handbook GARMIN GTX 327Transponder XTRA EXTRA 300LT
143. ft Roll 50ft Roll 50ft Roll 50ft Roll 50ft Roll 50ft Roll 50ft SL 111 191 124 213 138 238 153 264 169 292 187 322 205 354 2000 610 129 222 144 249 161 277 178 308 197 340 218 375 239 413 4000 1219 150 259 168 290 188 324 208 360 231 398 255 439 280 483 6000 1829 176 304 197 340 220 380 244 422 271 467 299 516 329 567 8000 2438 215 371 241 416 269 464 299 516 331 572 366 631 403 695 10000 3048 264 455 295 510 330 569 367 633 407 701 449 775 495 854 Weight 950 kg 2095 Ibs Rotating speed 70 KIAS 130 km h OAT gt 20 C 4F 10 C 14 0 C 32 10 C 50 20 C 68 30 C 86 40 C 104 F PA ft m Roll 50ft Roll 50ft Roll 50ft Roll 50ft Roll 50ft Roll 50ft Roll 50ft SL 125 216 140 241 156 269 173 298 191 330 211 364 232 400 2000 610 146 251 163 281 182 313 202 348 223 385 246 425 271 467 4000 1219 170 293 190 328 212 366 236 407 261 450 288 497 317 546 6000 1829 199 344 223 385 249 429 277 477 306 528 338 583 372 642 8000 2438 243 420 273 471 304 525 338 584 375 647 414 714 456 786 10000 3048 298 514 334 576 373 644 415 716 460 793 508 877 560 966 5 8 Page Date 6 April 2010 Pilot s Operating Handbook
144. g on location see below SELECTING ASQUAWK CODE The selected squawk code will always be in use As you change the squawk code the original code will be used untill you are finished selecting the new code Touch the transponder squawk code window at the top of the display 2 The XPDR page will be displayed The Squawk Code value will be active for selection for use by the active transponder 3 Touch the numeric keypad or use the rotary knobs to select the desired Squawk Code 4 Then touch Enter or press the small right knob 5 The selected Squawk Code will be shown in the XPDR window at the top of the display Page Date 6 November 2012 922 11 Section 922 Pilot s Operating Handbook GARMIN GTN 635 650 750 XTRA EXTRA 300LT IMPORTANT CODES 1200 The VFR code for any altitude in the US Refer to ICAO standards elsewhere 7000 The VFR code commonly used in Europe Refer to ICAO standards 7500 Hijack code Aircraft is subject to unlawful interference 7600 Loss of communications 7700 Emergency 7777 Military interceptor operations Never squawk this code 0000 Military use Not enterable Avoid selecting code 7500 and all codes in the 7600 7777 range These trigger specialindicators 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 sh
145. ge Date 6 April 2010 910 5 Section 910 Pilot s Operating Handbook NAT AA83 001 Intercom XTRA EXTRA 300LT 910 7 2 OPERATION VOX OPERATION The VOX control is used to set the level of audio required to activate the microphones The AA83 001 provides three modes of intercom operation selected by the position of the VOX control LIVEICS When the VOX control is positioned fully ccw to the LIVE position all mics will be live and any sound picked up will be processed by the ICS system hot mic KEYED ICS When the VOX control is positioned fully cw to the MAX position the intercom will be in a keyed only mode VOX ICS When the VOX control is positioned between fully cw and fully ccw the intercom is in VOX mode To establish the VOX threshold rotate the control ccw until the LED turns red and then rotate the control cw until the LED goes dark Continue turning the control cw until the desired voice sensitivity is set NORMAL OPERATION In normal use the AA83 001 serves as a common intercommunication system and a flow through interface for connection to the ship s external communication system The NORM mode default permits everyone on the system to talk to each other listen to music and hear all radio communications Radio transmit functions may be initiated by either the pilot or the copilot The pilot has priority In NORM mode external tie line users are included in the ICS communications PIL ISO PILOT ISO
146. ged 2 on the upper edge and latched by two lockes 3 4 on the lower edge The front lock is a key lock 4 In the open position the door can be hold in place by a support rod 13 which is plugged into a hole 12 atthe forward edge of the door frame This rod is fastened by a clamp 15 atthe inside of the door when not in use The inside of the door also carries the baggage compartment placard 14 To open the door 1 Unlock the front lock 4 with the key if applicable 2 Press the buttons on the locks 5 3 Swivel up the door and secure in the upper position by fastening the support rod 12 13 To close the door 1 Fasten the support rod 13 in the clamp 15 inside the door 2 Swiveldownthe door 3 Close the locks by pressing down the lock levers 6 4 Lock the front lock 4 with the key if applicable Three tie down straps 9 and a baggage net are provided to secure baggage and other items in the compartment The two tie down straps in the main partition are arranged diagonally The straps are guided through slotted anchor plates 10 and can be fastened and tightened by cam buckles 9 Eye bolts 8 10 are provided in which the baggage net hooks can be clipped YN CAUTION If not adequately restrained baggage compartment items may pose a projectile hazard to cockpit occupants and or the aircraft structure in the event of rapid deceleration Secure all baggage items with tie down straps and the baggage net Us
147. gzeugproduktions und Vertriebs GmbH considers acrobatics without wearing an approved parachute to be unsafe 2 16 BAGGAGE The use of baggage is limited to operation in the normal catgegory The maximum baggage mass is limited to 10 kg 22 Ibs of low density items 2 16 Page Date 6 November 2012 Pilot s Operating Handbook XTR A EXTRA 300LT Paragraph 3 0 3 0 1 3 0 2 3 1 32 3 2 1 3 2 2 3 2 3 3 2 4 3 2 5 3 3 3 3 1 3 3 2 3 4 3 4 1 3 4 2 3 4 3 3 5 3 5 1 3 6 3 7 3 8 3 9 SECTION 3 EMERGENCY PROCEDURE Table of Contents Page INTRODUCTION ENSE LET 3 3 EER C M e 3 3 General Behaviour in Emergency Situations iese see ee RA ee ee cn non rn ee cn naar nn 3 3 AIRSPEEDS FOR EMERGENCY OPERATION ees eene see eek na ee ee kaak ee EER eek RR ee ee kke ee KERE 3 4 OPERATIONAL CHECKLIST io iese s vial deeg 3 4 Engine Failure during Take off Roll oooooonnnncocccnnonnomonccccnnnnnncncrcnnnn rene 3 4 Engine Failure immediately after Lake oft 3 4 Engine Failure during Flight Restart Process sees ee ee se ee ee ee ee ee ee e 3 4 Oil System Malfunction ee ee ee RA nennen RA ee aa ar ee ee Ba ee ee ee nnne nen 3 5 Altermator RAMU E 3 5 FORCED LANDINGS foresee ces ee edel 3 5 Emergency Landing without Engine Power 3 5 Precautionary Landing with Engine Power 3 6 ARE A A Ed PO OPT 3 6 Duri
148. h On Off Function and NAV ID On Off Keys Home Display GARMIN HOME Key Photo Sensor SD Card Message y EE 8 Direct To Key Annunciation And Key 271 HIT S Large and Small Locking Ee s Knobs Screw Annunciations Hints Xpdr Panel Controls Figure 1 GTN 6xx Display Layout All GTN units can be used to control the remote transponder GTX 33 The GTN 650 amp 750 also feature NAV functionality Additionally the GTN 750 can be used to display Charts and to control the optional GMA 35 remote audio panel Thissupplementis written for main software version 2 00 GPS software version 4 0 COM software version 2 01 and NAV software version 6 01 andis not suitable for earlier software versions Some differences in operation may be observed when comparing the information in this supplementto later software versions Verify the information herein with the GTN Series Pilot s Guide amp Cockpit Reference Guide GTN 6xx P N 190 01004 03 Issue B amp P N 190 01004 04 Issue C GTN 750 P N 190 01007 03 Issue B amp P N 190 01007 04 Issue B you received with your unit There you will also findfurther information 922 2 LIMITATIONS This supplement does not grant approval for IFR operations Page Date 6 November 2012 922 3 Section 922 Pilot s Operating Handbook GARMIN GTN 635 650 750 XTRA EXTRA 300LT Active Com Channel Standby Nav Standby Com Active Nav Channel Channel Channel Volume Squ
149. he situation In any emergency situation contact should be established with a ground station as soon as possible after completing the initial corrective action Include position altitude heading speed nature of the emergency and pilot s intentions in the first transmission There after the ground station should be kept informed of the progress of the flight and of any changes or developments in the emergency Three basic rules apply to most emergencies and should be observed by each aircrew member 1 Maintain aircraft control 2 Analyze the situation and take proper action 3 Land as soon as possible as soon as practical The meaning of as soon as possible and as soon as practical as used in this section is as follows Land AS SOON AS POSSIBLE ASAP Emergency conditions are urgent and require an immediate landing at the nearest suitable airfield considering also other factors such as weather conditions and aircraft mass Land AS SOON AS PRACTICAL Emergency conditions are less urgent and in the aircrews judgement the flight may be safely continued to an airfield where more adequate facilities are available AN WARNING Make only one attempt to restore an automatically disconnected power source or reset or replace an automatically disconnected CPD circuit protection device that affects flight operations or safety Each successive attempt to restore an automatically disconnected power source or the resetting of an automaticall
150. he upper left corner of the display while the IDENT mode is active VFR Sets the transponder code to the pre programmed VFR code selected in Configuration Mode this is setto 7000 atthe factory Pressing the VFR Key again restores the previous identification code FUNC Changes the page shown on the right side ofthe display Display data includes Pressure Altitude Flight Time Count Up and Count Down timers Also displays Contrast and Display if manual control and backlighting is selected in the installation configuration START STOP Starts and stops the Count Up Count Down and Flight timers CRSR Initiates starting time entry for the Count Down timer and cancels transponder code entry CLR Resets the Count Up Count Down and Flight timers Cancels the previous keypress during code selection and Count Down entry Returns cursor to the fourth code digit within five seconds after entry 8 Reduces Contrast and Display Brightness when the respective fields are displayed if manual control is selected in the installation configuration and enters the number eight into the Count Down timer 9 Increases Contrast and Display Brightness when the respective fields are displayed if manual controlis selected inthe installation configuration and enters the number nine intothe Count Down timer 914 1 4 FUNCTION DISPLAY PRESSURE ALT Displays the altitude data supplied to the GTX 328 in feet hundreds of feet i e flight level or
151. ie Ny reduce throttle 90 diving Vs Vue 1 reduce throttle 1 4 Loop climb 100 185 190 352 WE Loop 100 185 190 352 nO Stall turn 100 185 190 352 e Aileron roll 80 148 Va y full deflection Snap roll 80 148 140 259 e tail slide 100 185 190 352 i WE Spin Vs P Inverted spin 80 148 gei Knife edge gt 150 278 e e 10 seconds Inverted Flight gt 80 148 190 352 e 4 minutes 2 9 LOADFACTOR 2 9 1 NORMAL FLIGHT MTOW 950 kg 2095 Ibs 69 39 2 9 2 ACROBATIC FLIGHT Category MTOW 820 kg 1808 lbs Category Il MTOW 870 kg 1918 lbs Category III MTOW 950 kg 2095 lbs 10g 10g for 1 seat occupied 8g 8g for 2 seat occupied 6g 6g for 2 seat occupied Page Date 6 April 2010 Section 2 Pilot s Operating Handbook Limitations XTRA EXTRA 300LT 2 10 FLIGHT CREW LIMITS Minimum crew is one pilot in the rear seat Solo flying from rear seat only Maximum 2 persons are allowed For hearing protection noise supression passive or active communication headsets are required The rear cockpit is equipped with a complete set of airplane controls and instruments 2 11 KINDS OF OPERATIONAL LIMITS Only VFR flights at day are allowed The A C may be operated at OAT from 20 C 4 F to 44 C 111 F Below temperatures of 10 C 414 F the oil vent line must be modified by the low temperature kit breather line Flight in known icing conditions is
152. 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 Uptimer 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 forthe Count Down timer and cancels transponder code entry Returns cursorto 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 sele
153. ind Encoder ACK A 30 8 or higher 32960 0 20 1 50 O Page Date 18 June 2013 6 13 Section 6 XTRA Pilot s Operating Handbook Weight and Balance and Equipment List EXTRA 300LT QTY ITEM MANUFACTURER MODELNO PARTNO WEIGHT ARM INST R kg m O A 1 Transponder Antenna Comant Industries CI 105 32269 0 11 0 14 O 1 ELT Artex ME 406 32173 PG 1 42 2 60 O ELT Antenna for Artex Artex 110 773 33524 0 08 3 00 O 1 ELT KANNAD 406 AF COMPACT 34210 1 11 2 97 A 1 ELT KANNAD 406 AF INTEGRA 34422 0 99 2 96 A 1 ELT Antenna Rami AV 200 33965 0 08 3 00 AO for Artex or KANNAD 1 Intercom Northern Airborne NAT AA83 001 31659 PG 0 28 1 55 O 1 Panel Dock AirGizmos GPSMAP 696 33665 0 25 1 60 O 1 Panel Dock AirGizmos GPSMAP 796 34175 0 27 1 60 O 1 Panel Dock AirGizmos iPad Mini Panel Dock 34410 0 12 1 62 O 1 Remote Audio Panel Garmin GMA 35 33902 PG 1 00 1 53 O Cowling 54 1 Cowling lower incl Landing light provision Extra 8D001 020 VB 6 00 0 57 R Canopy 56 1 Standard Canopy Extra 26301 000 VF 13 50 1 69 1 Single Seat Canopy Extra 86411 001 VF 13 20 1 69 A Propeller 61 1 3 Blade Propeller MT Propeller MTV 9 B C C198 25 32285 30 50 1 15 R 1 Spinner MT Propeller P 810 2 31415 0 80 1 20 R 1 Governor MT Propeller P 880 5 31509 1 10 0 91 R 1 Governor Woodward A 210988 01209 1 10 0 91 A Engine 72 4 Powerplant 71
154. ind also further information Page Date 6 April 2010 914 3 Section 914 Pilot s Operating Handbook GARMIN GTX 328 Transponder XTRA EXTRA 300LT 914 1 1 MODE SELECTION KEYS OFF Powers off the GTX 328 Pressing STBY ON or ALT Key powers on the transponder displaying the last active identification code STBY Selects the standby mode When in standby mode the transponder will not reply to any inter rogations ON Selects Mode A In this mode the transponder replies to interrogations as indicated by the Reply Symbol Replies do not include altitude information ALT Selects Mode A and Mode C In ALT mode the transponder replies to identification and altitude interrogations as indicated by the Reply Symbol Replies to altitude interrogations include the standard pressure altitude received from an external altitude source which is not adjusted for barometric pressure Any time the function ON or ALT is selected the transponder becomes an active part of the Air Traffic Control Radar Beacon System ATCRBS The transponder also responds to interrogations from TCAS equipped aircraft 914 1 2 CODESELECTION Code selection is done with eight keys 0 7 providing 4 096 active identification codes Pushing one of these keys begins the code selection sequence Digits that are not yet entered appear as dashes The new code is activated when the fourth digit is entered Pressing the CLR Key moves the cursor back to the previ
155. ining tachometer to determine magneto ignition problems Quickly pressing and releasing the left button L causes the tachometer to mask the left tachometer Quickly pressing and releasing the right button R causes the tachometer to mask the right tachometer Dimmer DIM Quickly pressing and releasing the middle button D M causes the tachometer to alternately dim or brighten the LED indicators except the large red LED of the rpm Range 906 8 HANDLING SERVICING AND MAINTENANCE Not affected Page Date 6 April 2010 Section 906 Pilot s Operating Handbook Digital RPM Indicator XTRA EXTRA 300LT Left blank intentionally 906 6 Page Date 6 April 2010 m cM EXTRA SECTION 907 SMOKE SYSTEM Table of Contents Paragraph Page 907 1 GENERAL coin ana 907 3 907 2 LIMITATIONS ii id 907 3 907 3 EMERGENCY PROCEDURES ooo esse ee een ees Ese ee ee ee kk RE Ese aAA ee kk EE See Gee eek RE ESE Gee eek RR EE Ee Gee Gee KA 907 3 907 4 NORMAL PROCEDURES 5 ts ese ies In Ruine e XE Ee eek SEE wee Ce eeue ee ees TEENS Geen ig 907 4 907 5 sae oa RE M 907 5 907 6 WEIGHT AND BALANDGE 2 etico eere erasa ie cad 907 5 907 7 DESCRIPTION OF THE SYSTEM 1 ee ee ere erdt ad 907 5 907 8 HANDLING SERVICING AND MAINTENANCE see ee ee ee ee ee ee ee ee ese ee ee ee 907 7 Page Date 6 April 2010 907 1 Sectio
156. ion 917 Pilot s Operating Handbook ASPEN EFD1000 500 System XTRA EXTRA 300LT Left blank intentionally 917 2 Page Date 6 April 2010 Pilot s Operating Handbook Section 917 EXTRA 300LT XTRA ASPENEFD1000 500 System 917 1 GENERAL This Airplane Flight Manual Supplement AFMS applies to avionics installations of the following display combinations EFD1000 PFD Pilot EFD1000 PFD Pilot and EFD500 MFD EFD1000 PFD Pro EFD1000 PFD Pro and EFD500 MFD EFD1000 PFD Pro and EFD1000 MFD OP ONS The Evolution Flight Display System is a multi display highly capable Electronic Flight Instrument System EFIS with integral Micro Electromechanical Systems MEMS based Air Data Attitude and Heading Reference System ADAHRS with an internal backup battery The EFD 1000 PFD Pilot offers a state of the art Flight Display with attitude indication and slaved Directional Gyro with mapping The EFD 1000 PFD Pro offers a HSI two pointer RMI instead of the Directional Gyro When combined with the optional EFD 500 MFD the system offers a multi panel Multi Function Display solution that displays high resolution moving maps with Jeppesen enroute and terminal data as well as relative terrain depictions When combined with the optional EFD 1000 MFD an independent redundant ADAHRS source provides secondary attitude information and a secondary HSI display atthe push of a button The EFD1000 MFD can instantly revertto afully functio
157. ion appears on the map and terrain display pages as red and yellow tiles or towers and is depicted for advisory use only Aircraft maneuvers and navigation must not be predicated upon the use of the terrain display Terrain proximity and obstacle information is advisory only The terrain display is intended to serve as a situational awareness tool only By itself it may not provide either the accuracy or the fidelity on which to base decisions and plan maneuvers to avoid terrain or obstacles 922 2 4 TRAFFIC TIS ONLY Traffic may be displayed on the GTN when connected to an approved optional TIS traffic device This system is capable of providing traffic monitoring and alerting to the pilot Traffic shown on the display may or may nothave traffic alerting available The display of traffic is an aid to visual acquisition and may not be utilized solely for aircraft maneuvering 922 2 5 FLIGHTPLANNING CALCULATION FUNCTIONS When using the calculator planner pages data must be entered into all data fields and verified by the pilot prior to use of the data The pilot must verify the desired altitude and appropriate barometric pressure setting to ensure valid calculations Aircraft performance or fuel loading must not be predicated upon the use of data derived from these functions Page Date 6 November 2012 922 5 Section 922 Pilot s Operating Handbook GARMIN GTN 635 650 750 XTRA EXTRA 300LT 922 2 GLOVEUSE No device may be used
158. ions 7500 Hijacking 7700 Emergency All secondary surveillance radar sites are ready to receive this code at all times See the Airman s Information Manual AIM for a detailed explanation of identification codes 915 4 NORMAL PROCEDURES Not applicable 915 5 PERFORMANCE Not applicable Page Date 6 April 2010 915 7 Section 915 Pilot s Operating Handbook GARMIN GTX 330 Transponder XTRA EXTRA 300LT Left blank intentionally 915 8 Page Date 6 April 2010 Pilot s Operating Handbook X TRA EXTRA 300LT Paragraph 916 1 916 2 916 2 1 916 3 916 3 1 916 3 2 916 4 916 5 916 6 916 7 916 7 1 916 7 2 SECTION 916 GARMIN GNC 420W GNS 430W Table of Contents Page GENERAL R PON 916 3 B arigen m c ee EE 916 3 PIACANOS D EE EE EE EE N HAK Laa 916 4 EMERGENCY ABNORMAL PROCEDURES ese sees ees se eek R Rae ee kk Raak ee Rae ee RE see ek kke ae ee Ee 916 4 Emergency Procedures Es EE tei cento tme Og xe te toes o Ryu uia ace SR KA Ee Oe Ra SEEN GEE ee 916 4 Abnormal Procedure TTT 916 4 NORMAL PROCEDURES 0 Ee 916 5 PERFORMANCE Ke N EE 916 5 WEIGHT amp CENTER OF GRAVITY oscila 916 5 SYSTEM DESCRIPTION 222i see ese nece pnm e aeneo canem c aano o cuu sete eo vacua sea ken anina 916 5 EI eene nennen nennen rennen trenes ee ee 916 5 Default Nav Page iii 916 7 Page Date 6 April 2010 916 1 Section 916 Pilo
159. ions are to be performed The Table of Contents shows all EXTRA Supplements available for the EXTRA 300LT A check mark in the Section column indicates that the corresponding supplement must be included in this POH Page Date 6 April 2010 9 3 Section 9 Pilot s Operating Handbook Supplements XTRA EXTRA 300LT Left blank intentionally 9 4 Page Date 6 April 2010 Eee EXTRA SECTION 901 STEERABLE TAIL WHEEL Table of Contents Paragraph Page 901 1 GENERAL usuaria dune EORR Ee adus aida Ee 901 3 901 2 LIMITATION PER EE A E a 901 3 901 3 EMERGENCY PROCEDURES ees Ese ee ee eek RR EE Bee Gee ee kke ESEG Gee ee sas Ee enn ee RR EE Ee Gee Gee KA 901 3 901 4 NORMAL PROCEDURES cuicos 901 3 901 5 PERFORMANCE EE dd da 901 3 901 6 WEIGHT AND BALANCE EG icona eiii 901 3 901 7 DESCRIPTION OF THE SYSTEM oscilar 901 3 901 8 HANDLING SERVICING AND MAINTENANCE see ee ee ee ee ee eene nennen nnne 901 4 Page Date 6 April 2010 901 1 Section 901 Pilot s Operating Handbook Steerable Tail Wheel XTRA EXTRASOOLT Left blank intentionally 901 2 Page Date 6 April 2010 Pilot s Operating Handbook Section 901 EXTRA 300LT XTRA 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 handling quality the EXTRA 300LT can be equipped with a
160. ircraft to ATC A triangle on the left next to the code signals the transponder replies SQUAWKIDENT 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 1 Thefollowing differenttests are integrated inthe transponder orcanbetriggered atthe 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 Page Date 6 April 2010 911 7 Section 911 F Pilot s Operating Handbook BECKER ATC 4401 Transponder XTRA EXTRA 300LT 2 Apermanenttestruns inthe 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 3 A further test of the unit is triggered if the VFR1 button F and VFR2 button G are pressed simultaneously At this test all segments must flash into display E as long as the buttons are pushed Additional the transmitter and evaluation are tested on correct function in the SBY ON and ALT modes 4 Incase of a failure appears the report e g E10 in the top line of the display Switch OFF the transponder at such
161. it 7 10 6 MIXTURE Vernier control located at the left side of the rear cockpit red knob 7 10 7 RPM CONTROL Vernier control on the left side of the rear cockpit Preselection of RPM possible due to constant speed governor blue knob 7 10 8 FUELSELECTOR VALVE Dual control A rotary fuel selector valve is mounted behind the firewall on the right side of the fuselage A torque tube connects the valve to both cockpit handles Pull and turn the handle 90 to open the valve to the Acro amp Center Tank A further 90 turn switches to the Wing Tankfuel supply Position down CLOSED Position left ACRO amp CENTER TANK Position up WING TANK 7 10 9 EXHAUSTSYSTEM A complete Gomolzig 6 in 1 System with integrated silencer is installed on the 300LT 7 11 FUELSYSTEM The fuel system refer to Figure 3 consists of two separate independent tanks Acro amp center tank in the fuselage Wing tank LH and RH 7 10 Page Date 22 April 2015 Section 7 Description and Operation of Aircraft and Systems Pilots Operating Handbook EXTRA 300LT XTRA HI ANVL 9NIM d 1801 YIDNASNVHL ALO 13N4 192 A TIVI quvOSMN3AO SANIT LNSA TI3HS NOILOALOYd dd49 IWNOILIGGV NV 34N1V34 SMNVL OOV ANY HALNAO LON DT 3N AIdANS Tand HOLOZIFNI NSAING 3NION3 dWiNd 13N4 dIAMd 13N4 919419313
162. ization If the measured values are above the warning limit and below the alarm limit an intermitted sound is heard on the head set and the G V LIMIT WARNING LIGHT flashes If the measured value exceeds the alarm limit a continuous sound is heard on the head set and the G V LIMIT WARNINGLIGHT illuminates continuously When the alarm warning has been activated the instrument will display a service message after the next turn on of the instrument to inform the user of the exceeded acceleration The USER BUTTON is programmed in the main set up to display the minimum and maximum acceleration overview MEMORY Thefollowing memory types are included inthe TL 3424 EXT 1 A long term memory storing the last recorded 30 minutes 20 000 lines entries every 0 1 seconds 2 A Scheck Report storing all cases of limit exceedance and the values in the immediate vicinity ofthis event 160 lines per case 3 A Line Report storing the last 64 values of limit exceedance acceleration and speed A rolling type memory is used This means that in case the available memory capacity is exceeded the oldest memory lines will be overwritten PRESETTINGS Thefollowing values or definitions are presetin the special configuration ofthe TL 3424 EXT WARNING MAX WARNING MIN ALARM MAX ALARMMIN SPEEDLIMIT Record begins at LANGUAGE SAMPLE RATE 49 5g 9 5g 10 1 g 10 1g 220KIAS 50 KIAS English 0 1 Page Date 9 Aug
163. k X TRA EXTRA 300LT Paragraph 917 1 917 1 1 917 2 917 2 1 917 3 917 4 917 5 917 6 917 7 917 7 1 917 7 2 917 7 3 917 7 4 917 7 5 917 7 6 917 7 7 917 7 8 917 7 9 917 8 SECTION 917 ASPEN EFD1000 500 Table of Contents Page icd zl d 917 3 Equipment Configuration sesenta 917 4 Bi apape e e 917 4 Placards and Decals EE 917 4 EMERGENCY PROCEDURES ette aia 917 6 NORMAL PROCEDURES cheeses be aia 917 6 PERFORMANCE cio EE N OE EE 917 6 WEIGHT 8 CENTER OF GRAVITY A esse sesse een see ee ek Rae RR RE Re RR E EER AAR Re RARR Ra R KERE ee annan 917 6 SYSTEM DESCRIPTION 0000 917 6 E EE 917 6 Pitot Obstruction Monitor Configuration 5 only ee ee Re ee ee ee ke 917 6 Databases EFD1000 500 MED Only 917 7 RSM GPS HE EE EE OR EE N ET N 917 8 Operation on Internal Battery i s ceca seeded ad erecto ku sed K race dus aa d 917 8 Geographic Reservation aaaaaaaaaaasaaasssanasnannanannnnsnnnnnnnnnnnnnnnanannnnnninnnnnnannnnsannnsnananaaa 917 9 Hazard Awareness EFD1000 PFD PRO and MFDs ONLY seen 917 9 Evolution Synthetic Vision Optional iss ee see ee ke ee ee ee ee RA ee Re ee ee ee nnne 917 11 Aspen PFD as Encoded Altitude Gource see esse dek de aia 917 12 HANDLING SERVICING AND MAINTENANCE ees ees een ese ee ek ea eek ee KERR EER Ee eek RR ae ee ee 917 12 Page Date 6 November 2012 917 1 Sect
164. k Section 911 XTRA BECKER ATC 4401 Transponder EXTRA 300LT 911 1 4 911 1 5 911 1 6 911 1 7 Avoid selecting code 7500 and all codes in the 7600 7777 range These trigger specialindicators 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 FLIGHT OPERATION IN MODE A TRANSPONDER REPLY CODE ONLY 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 OPERATIONIN MODE A C REPLY CODE AND ALTITUDE CODE 1 2 Select squawk as described above ATC requests the transmission alpha charlie or charlie switch the transponder to ALT using mode switch A The transponder replies using the code set and in response to mode C requests it tansmits the flight level of the a
165. l 2010 903 3 Section 903 Pilot s Operating Handbook Cabin Heating System X TRA EXTRA 300LT 903 7 SYSTEMDESCRIPTION On the left front engine baffle a 3 air intake 1 figure 1 with screen is positioned From there fresh air is routed through a 3 ducting 2 to the exhaust muffler heat shroud 3 where itis heated up A selector box 4 is placed on the engine side of the firewall Using the main handle 9 the warm air can there be guided into the cockpit or dumped overboard A further selector box 5 is located onthe aft side of the firewall Using the distribution handle 8 the ratio of warm air supply between front and rear can be controlled there The rear selector box incorporates the warm air dispensers for the front occupant as well as the flange for the 2 ducting 6 to the air outlets 7 atthe pilot s feet 2 e d G 3 gt 4 gt AN e Firewall 5 AL NL A J T E fwd rm 7 a g Figure 1 903 8 HANDLING SERVICING AND MAINTENANCE Not affected 903 4 Page Date 6 April 2010 Pilot s Operating Handbook X TRA EXTRA 300LT Paragraph 904 1 904 2 904 3 904 4 904 5 904 6 904 7 SECTION 904 ACCELEROMETER TL 3424 EXT Table of Contents Page GENERALE nea a uic RRR 904 3 LIMITATIONS eiii 904 3 EM
166. 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 modethe transponder repliesto interrogations as indicated by the Reply Symbol Replies do not include altitude information Page Date 6 April 2010 913 3 Section 913 Pilot s Operating Handbook GARMIN GTX 327Transponder XTRA EXTRA 300LT ALT Powers on the transponder in Mode A and Mode C At power on the last active identification code will be selected In ALT mode the transponder replies to identification and altitude interrogations as indicated by the Reply Symbol Replies to altitude interrogations include standard pressure altitude received from a separate encoder 913 1 2 CODESELECTION 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 digitis 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 CODE
167. layed 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 GTX 328 owner accepts all responsibility for obtaining the proper license before using the transponder The coverage you can expect from the GTX 328 is limited to line of sight Low altitude or aircraft antenna shielding by the aircraft itself may result in reduced range Range can be improved by climbing to a higher altitude It may be possible to minimize antenna shielding by locating the antenna where dead spots are only noticed during abnormal flight attitudes YN CAUTION The GTX 328 should be turned off before starting or shutting down aircraft engine TheGTX328 Transponder is automatically powered on by the respective AVIONIC switch or when previously manually powered off while AVIONIC switch is on by pressing the STBY ALT or ON keys After power on a start up page will be displayed while the unit performs a self test This supplement is written for software version 5 00 or later andis not suitable for earlier software versions Some differences in operation may be observed when comparing the information in this supplementto later software versions Verify the information herein with the GTX 328 pilot s guide PN 190 00420 03 applicable revision you received with your transponder There you f
168. le Page Date 6 April 2010 XTRA Pilot s Operating Handbook EXTRA 300LT MAIN TABLE OF CONTENTS Section 1 GENERAL 2 LIMITATIONS 3 EMERGENCY PROCEDURES 4 NORMAL PROCEDURES 5 PERFORMANCE 6 WEIGHT amp BALANCE EQUIPMENT LIST 7 AIRPLANE amp SYSTEMS DESCRIPTIONS 8 AIRPLANE HANDLING SERVICE amp MAINTENANCE 9 SUPPLEMENTS Page 2 1 3 1 5 1 6 1 8 1 9 1 vi Page Date 6 April 2010 EXTRASQQUT XTRA SECTION 1 GENERAL Table of Contents Paragraph Page 1 0 DESCRIPTION me 1 3 1 1 SPECIFICATION OF CLASS iii a dee ee dd de Ge ee 1 3 1 2 MANUFACTURER conil oi 1 3 1 3 Zei elle BA EE 1 3 1 3 1 E EE O 1 3 1 3 2 Milla BE ER AA ai AA EA MR AR EK 1 4 1 3 3 lm N 1 4 1 3 4 Horizontal Tall ein aaron OER OE RO EE EE 1 4 1 3 5 Elevator Ee ede eee ER N N OE OE A OE N N 1 4 1 3 6 Venice EE Se EE ie ED ae 1 4 1 3 7 Ridder EE ee Le 1 4 1 4 ENGINE 111271 1 5 1 5 inizia 1 5 1 5 1 Exnaust EIN EU 1 5 1 6 FUEL EE EE EE 1 5 1 7 OIL E PPP TREE aR 1 5 1 8 Roy eN 1 6 1 9 TERMINOLOGY ee 1 6 1 10 SECONDARY TERMINOLOGY ie sessie de ee n ede de de in an nnn ed dee i caa n bk dd 1 7 1 11 GONVERSION TABLE iiaeiai ecc sesde ees ncn acc unn p
169. lect the aircraft by its Aircraft Address assigned to the aircraft by the aviation agency Itoperates onradar frequencies receiving ground radar interrogations at 1030 MHz andtransmitting a coded response of pulses to ground based radar on a frequency of 1090 MHz The GTX 330 is equipped with IDENT capability that activates the Special Position Identification SPI pulsefor 18 seconds Mode S transmit receive capability also requires 1090 MHz transmitting and1030 MHz receiving for Mode S functions In addition to displaying the code reply symbol and mode of operation the GTX 330 screen will display pressure altitude and timer functions The displayed pressure altitude may not agree with the aircraft s baro corrected altitude under non standard conditions The unit also features flight timers The Traffic Information Service TIS is not available in this installation NOTE The GTX330 owner accepts all responsibility for obtaining the proper license before using the transponder The coverage you can expect from the GTX 330 is limited to line of sight Low altitude or aircraft antenna shielding by the aircraft itself may result in reduced range Range can be improved by climbing to a higher altitude It may be possible to minimize antenna shielding by locating the antenna where dead spots are only noticed during abnormal flight attitudes N CAUTION The GTX 330 should be turned off before starting or shutting down aircraft engine The
170. ls VOX for the pilot only For full information on VOX operation see section 910 7 2 below MUSIC VOL COPILOT VOX This control is a fluted concentric rubber knob on the bottom of the panel The inner front knob is the MUSIC VOL control which is used to set normal music volume The volume can be adjusted from minimum fully ccw to maximum fully cw The outer rear knob is the COPILOT VOX control that controls VOX for the copilot and passengers For full information on VOX operation see section 910 7 2 below ANNUNCIATOR The panel annunciator is a bi colour LED that shows intercom status Ifthe LED is illuminated green itindicates transmit activity and if itis red itindicates VOX activity For transmit with sidetone or mic activity it will illuminate amber The green LED also indicates a possible stuck mic if still lit after transmission is concluded MODE CONTROL The mode controlis a three position toggle switch used to select the operational mode of the unit The selectable positions are SPLIT PIL ISO and NORMAL These modes are described fully in section 910 7 2 below PTT SWITCHES PTT Switches are installed on the control sticks They are used for radio transmittions Further PTT switches are installed on the power levers and are used for the intercom SOCKETS Dual sockets for connecting the headsets are installed on the right side of each seat The aft cockpit also features a receptacle for music input Pa
171. mber2012 921 1 thru 921 6 31 May 2012 922 1 thru 922 16 6 November 2012 924 1 thru 924 8 22 April 2015 Page Date 22 April 2015 Pilot s Operating Handbook EXTRA 300LT XTRA Left blank intentionally Page Date 6 April 2010 X TR A Pilot s BE INTRODUCTION This handbook contains 9 sections and includes the material required to be furnished to the pilot by FAR Part 23 It also contains supplementary data supplied by EXTRA Flugzeug produktions und Vertriebs GmbH THIS MANUAL IS FURNISHED TO THE CIVIL AVIATION AUTHORITIES AS APART OF THE CERTIFICATION MATERIAL FOR THIS MODEL NOTES This Flight Manual applies only to the aircraft whose nationality and registration marks are noted on the title page This Flight Manual is only valid in connection with the latest approved revision Refer to the EXTRA Homepage directlink http www extraaircraft com techserv asp where the POH Revision Index always shows the current revision status It is the responsibility of the pilot to be familiar with the contents of this Flight Manual including revisions and any relevant supplements Pages of this Airplane Flight Manual must not be exchanged and no alterations of or additions to the approved contents may be made without the EXTRA Flugzeugproduktions und Vertriebs GmbH EASA approval The editor has the copyright of this Flight Manual and is responsibl
172. me knob controls audio volume for the selected COM radio or NAV receiver if installed andany external audio inputdevices if installed Whenthe COM radio is active press the Volume knob momentarily to disable automatic squelch control for the COM radio When the NAV radio is active press the Volume knob momentarily to enable disable the ident tone forthe NAV radio The large right and small right knobs are used for data entry and to set the frequencies for the communications transceiver or the VOR Localizer receiver if installed 922 8 Page Date 6 November 2012 Pilot s Operating Handbook Section 922 EXTRA 300LT XTRA GARMIN GTN 635 650 750 Squawk Code Window Squawk Code Active Ba kspace Key VER Squawk Transponder Code 1200 Key Selection Reply Annunciation Active XPDR Code and Numeric Keypad Mode Display Enter Key ENR IDEMO GPS PD Code Pal Erer P Context Sensitive Mode Key Instructions for Rotary Knob Figure 3 GTN 6xx XPDR Operation 922 7 2 SECURE DIGITAL CARD A Secure Digital SD card is used to load and store various types of data and for various database updates Ensure the GTN unitis powered off before inserting or removing an SD card 922 7 3 SELECTING COM NAV FREQUENCIES Tuning control normally remains in the COM window and will return after 30 seconds of inactivity USING KNOBS Press the small right knob momentarily to make the NAV window active for editing The stand
173. n 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 ff no valid Alis stored is displayed EN Flight Number or editable Company Call Sign can be replaced by Al 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 AIRCRAFT IDENTIFICATION AI OR FN With flight plan The definition out of the flight plan e g Flight Number or Company Call Sign Without flight plan VFR Tail Number Call Sign The indication of AU 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
174. n 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 6 April 2010 901 3 Section 901 Pilot s Operating Handbook Steerable Tail Wheel XTRA EXTRA 300LT 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 6 April 2010 mee EXTRA SECTION 902 ELECTRIC PEDAL ADJUSTMENT Table of Contents Paragraph Page 902 1 GENERAL iii id 902 3 902 2 LIMITATIONS iii 902 3 902 3 EMERGENCY PROCEDURES oue ode seek vie es kes ve see sku ke ve sedes kes KA be rd 902 3 902 4 NORMAL PROCEDURES 5 ii 902 3 902 5 PERFORMANCE PP 902 3 902 6 WEIGHT AND BALANDGE onore dida 902 3 902 7 DESCRIPTION OF THE SYSTEM see ee ee ee ese ee ee serene nnne nens nnne nnne nnns Ee Gee en 902 4 902 8 HANDLING SERVICING AND MAINTENANCE see ee ee serene nennen nennen nnne 902 4 Page Date 6 April 2010 902 1 Section 902 Pilot s Operating Hand
175. n 907 Pilot s Operating Handbook Smoke System XTRA EXTRA 300LT Left blank intentionally 907 2 Page Date 6 April 2010 Pilot s Operating Handbook Section 907 EXTRA 300LT X TRA Smoke System 907 SMOKESYSTEM 907 1 GENERAL For performing at airshows the EXTRA 300LT may optionally be equipped with a smoke System 907 2 LIMITATIONS For safe operation of the smoke system the following limitations have to be considered 1 The load factor and MTOW are limited to 8g 8g at 870kg ACRO II limited to single seat operation and 6g 6g at 950kg ACRO III 2 Specification of the smoke oil straight paraffin oil viscosity 30 50 cSt at 20 C 68 F initial boiling point gt 330 C 626 F For example Fauth FC05 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 Wearing a parachute is strongly recommended Operating Markings amp Placards SMOKE OIL PT External Next to the quick On switch of E connector at the fuselage bottom the throttle lever __ On instrument panel above control switch row On instrument panel SMOKE below control switch row MIA ES For SINGLE PUMP SYSTEM
176. n optional steerable tailwheel The deflection angle of this tailwheel is arranged by the rudder control up to plus minus 30 Exceeding this deflection the tailwheel has a full swivel capability by a release mechanism LIMITATION The operation limitations are not effected due to the use of the steerable tailwheel EMERGENCY PROCEDURES There is no change of basic emergency procedures with the installation of the steerable tailwheel NORMAL PROCEDURES There are no changes for the described normal procedures after installation of the steerable tailwheel In addition to the existing normal procedures the light precompression of connec tor springs and movement of the rudder have to be checked during the preflight check PERFORMANCE Changes in flight performance due to installation of the steerable tailwheel are not notice able The given basic performance data under section 5 are still valid WEIGHT AND BALANCE A change of the running empty weight and resulting C G position after installation of the steerable tailwheel is neglectable because of minor differences in weight and C G between standard and optional steerable tailwheel DESCRIPTION OF THE SYSTEM The 5 inch tailwheel has a solid rubber tire and is rotatable by means of a wheelfork which is connected to a bearing steelsleeve This steelsleeve itself contains also the release mechanic which gives the wheelfork a full swivel capability exceeding plus minus 30 deflectio
177. nal flight display generated from ADAHRS data completely independent of that generated by the PFD The EFD1000 Pilot PFD is a Flight Display with Attitude indicator heading indicator and moving map The Pilot PFD cannot be installed with an EFD1000MFD The EFD500 is afully functional MFD with allthe capability ofthe EFD1000 MFD except reversion HSI Remote Sensor Module RSM Cross Link information receive only and the air data attitude and heading features The standard internal battery inthe EFD1000 or EFD500 is capable of providing 30 or more minutes of operation at typical cockpit temperatures if aircraft power to the system fails An Emergency Backup Battery is not installed In the EXTRA 300LT the EFD1000 500 system is used as a secondary back up instrument system N CAUTION Due to the capabilities of the aircraft especially the extreme agility with high angular rates the EFD1000 500 System cannot be operated reliably in acrobatics Observe flags and reset EFD1000 500 System if required NOTE Dueto the location of the Remote Sensor Module RSM the outside air temperature data are available time delayed The EFD1000 500 System must utilize the software version described below or later approved versions The system software version for the Main Application Processor MAP and forthe Input Output Processor IOP both of which are contained within the EFD display head is displayed via the Main Menu SYSTEM STATUS page
178. nally during the 100h Check for the SINGLE PUMP SYSTEM Check the system for leakage lines fittings tanks Check the smoke oil tanks for proper attachment Cleantheoverpressure check valve if required remove oil residue Cleanthe injector nozzle if required remove carbon debris Cleanthe filter element After each flight with activated Smoke System Clean the aircraft belly fairing and the rudder cable from smoke oil contamination NOTE The rudder cables might suffer from increased wear when they are covered with smoke oil and dust Page Date 6 April 2010 907 7 Section 907 Pilot s Operating Handbook Smoke System XTRA EXTRA 300LT Left blank intentionally 907 8 Page Date 6 April 2010 mee EXTRA SECTION 908 SINGLE SEAT CANOPY Table of Contents Paragraph Page 908 1 GENERAL iii 908 3 908 2 LIMITATIONS ici 908 3 908 3 EMERGENCY PROCEDURES 4 5 seek vie es kes ve see sku ke ve sedes kes e be TR Eege EN 908 3 908 4 NORMAL PROCEDURES tiese ee aie cenit ds eed ak ds eed R NA ede ke See coc KRANAR 908 3 908 5 PERFORMANCE ees ee Gede Oe de Ge a 908 3 908 6 WEIGHT AND BALANCE AND EQUIPMENT LIST ees ees see ee ese ees ee ee ee see ee ee ee ee se Gee 908 3 908 7 DESCRIPTION OF THE SYSTEM sees ees sesse ee ee ee ee ese ee eek ee eke ee ee ee R KRK R RE ee ee en 908 3 908 8 HANDLING SERVICE AND MAINTENANCE esse ees see ees see ee see ees see ee s
179. nd acrobatic operation The pilot should be familiar with all procedures contained in this Pilot s Operating Handbook which must be carried on board The pilot has to comply with Checklist for daily check and inspections see Section 8 Handling Servicing and Maintenance Page Date 6 April 2010 Section 4 Pilot s Operating Handbook Normal Procedures XTRA EXTRA 300LT 4 1 PREFLIGHTINSPECTION 4 1 1 EXTERIORINSPECTION ILLUSTRATION 4 1 2 GENERAL Visually check airplane for general condition during walk around inspection Perform exterior check as outlined in the picture above in counterclockwise direction 4 2 CHECKLISTPROCEDURES 1 Cockpit 1 Pilot s Operating Handbook AVAILABLE 2 Airplane weight and balance CHECKED 3 Ignition switch OFF 4 Battery switch ON 5 Fuel quantity indicators CHECK 6 Battery switch OFF 7 Fuel selector ACRO amp CENTER TANK NOTE Although safe operation does not require the use of the tanks in a specific sequence itis recommended to set fuel selector to ACRO amp CENTER TANK position 2 Empennage 1 All round inspection canopy surfaces stabilizer elevator trim rudder and tailwheel CHECK 2 Horizontal stabilizer attachment bols CHECK FOR FREEPLAY BY MOVING THE TIP OF THE HORIZ STABILIZER UP AND DOWNWARDS 3 Baggage compartment CHECK EMPTY or baggage SECURED 4 Baggage compartment door CHECK CLOSED and LATCHED 3 Right Wing 1 Aileron freedom of movement a
180. nd security CHECK 4 4 Page Date 6 April 2010 it cid EXTRA Section 4 Normal Procedures Trailing edge Fueltank vent opening right landing gear Fuel quantity Fuel tank filler cap Wing fuel tank drain OO O PO 7 Right landing gear wheel 8 Stallwarning vane 4 Nose 1 Engine oil dipstick 2 Propeller and spinner 3 Air inlet 4 Acro amp center fuel tank drain 5 Fuel filter drain 6 Exhaust silencer 5 Left wing Leftlanding gear wheel and brakes Fuel quantity Fuel tank filler cap Wing fuel tank drain POND Pitotcover Trailing edge Aileron freedom of movement and security S O UI 6 Before starting engine Preflightinspection Passengerbriefing Parachute handling briefing Seats seatbelts shoulder harnesses Canopy Brake Battery switch Avionics power switch Electrical equipment Alternator Wingtip position Strobe lights AOOONDUOURONDA sch CHECK CHECK CHECK CHECK DRAIN FOR AT LEAST 4 SECONDS TO CLEAR SUMP OF POSSIBLE WATER CHECKCLOSED CHECK CHECK CHECK CHECK CHECK DRAIN FORAT LEAST 4 SECONDS TO CLEAR SUMP OF POSSIBLE WATER CHECKCLOSED DRAIN FOR AT LEAST 4SECONDS TOCLEARFILTER OF POSSIBLE WATER CHECKCLOSED CHECK FOR DAMAGE AND SECURE ATTACHMENT CHECK CHECK CHECK DRAIN FOR AT LEAST 4 SECONDS TO CLEAR SUMP OF POSSIBLE WATER CHECKCLOSED REMOVE CHECK CHECK COMPLET
181. ndicator 0 0 0 5 Vertical speed indicator 0 0 0 6 Turn and bank indicator 0 0 0 7 Artificial horizon 0 0 0 8 Directional gyro 0 0 0 9 Transponder 1 1 1 1 In some airspaces Mode S Elementary Surveillance functionality is required Page Date 6 November 2012 2 15 Section 2 Pilot s Operating Handbook Limitations XTRA EXTRA 300LT NORMAL ACROBATIC 1 seat 2 seats ENGINEINDICATION 1 RPM indicator 1 1 1 4 Manifold pressure indicator 1 1 1 2 Exhaust gas temperature indicator 0 0 0 3 Cylinder head temperature indicator 0 0 0 OIL 1 Oil temperature indicator 1 1 1 2 Oil pressure indicator 1 1 1 FLIGHT CREW EQUIPMENT 1 Parachute rear 0 2 Parachute front 0 0 li 3 Seat belt rear 1 1 1 4 Seat belt front 1 0 1 5 Headset rear 1 1 1 6 Headset front 1 0 1 NOTE The zeros 0 used in the above list mean that either the equipment or system or both were not required for type certification for that kind of operation Either equipment or systems in addition to those listed above may be required by the national operating regulations The asterisks used in the above list mean that latest national aviation regulations must be observed in determining whether the equipment and or system are required According FAR Part 91 General Operating and Flight Rules each occupant of an US registered airplane must wear an approved parachute when performing acrobatic maneuvers Extra Flu
182. nformation during turns transitions to climb or descent or acrobatics The intended function of the Terrain Warning System associated with the Evolution Synthetic Vision application is to provide warnings when the system predicts a collision with the terrain or an obstacle The Flight Path Marker is an integral part of this system and changes in shape and color Page Date 6 November 2012 917 11 Section 917 Pilot s Operating Handbook ASPEN EFD1000 500 System XTRA EXTRA 300LT if the aircraft continues on the collision path In addition the terrain is colored based on the aircraft proximity to the terrain yellow when the aircraft is within 500 feet vertically of the terrain or obstacle and red when the aircraft is within 100 feet vertically NOTE Synthetic Vision and the associated Terrain Warning System are dependant on accurate barometric altitude An inaccurate altimeter setting will cause an incorrect depiction of the elevation of terrain and obstacles Very cold temperatures can also cause significant errors in alimetry The pilot in command has the responsibility to use accepted visual procedures to avoid terrain and obstacles Obstacles less than 200 feet AGL are not displayed Terrain and obstacle information is intended to assist the flight crew in fulfilling the responsibility to avoid terrain and obstructions through visual means Pressing menu and selecting TWS INH will inhibit the Terrain Warning System
183. ng Start on Ground tre Ses dad 3 6 If Engine Fails to Start seed esse ee dese ee ee ee ee ek AA aa aaa ad enne R ee nnns nennen nnne 3 6 Engine Fire Ale GE EE EE ana 3 7 AA A EE 3 7 madvereni Icing e lu EE 3 7 UNINTENTIONAL SPIN neueren nanc oek gede kk ke een ke rixa eoru EER eed 3 7 MANUAL BAIL OUT ee 3 7 EMERGENCY EXIT AFTER TURN OVER esse aas ees sae eek ee see eek Ra Geek RR ee rca 3 8 ELEVATOR CONTROL FAILURE sissa gas slajka ee ne tana oo Re EE 3 8 Page Date 6 April 2010 3 21 Section 3 Pilot e Operating Handbook Emergency Procedures XTRA EXTRA 300LT Left blank intentionally 322 Page Date 6 April 2010 Pilot s Operating Handbook LL Section 3 EXTRA 300LT XTRA Emergency Procedures 3 0 INTRODUCTION 3 0 1 GENERAL This section contains the checklist and procedures coping with emergencies that may occur This checklist must be followed in various emergencies to ensure maximum safety for the crew and or aircraft Thorough knowledge of these procedures will enable the aircrew to better cope with an emergency The steps should be performed in the listed sequence However the procedures do not restrict the aircrew from taking any additional action necessary to deal with the emergency 3 0 2 GENERAL BEHAVIOURIN EMERGENCY SITUATIONS As soon as one of the crew member becomes aware that an emergency situation exists he must immediately alert the other crew member of t
184. no possibility of lost communication because of a lack of pilot action Note thatthe pilot s boom mic is sent directly to the radio in this mode and only a PTT key input is needed to transmit NOTE In this mode the receive sidetone levels may require adjustment at the audio source SPLIT OPERATION Operation in SPLIT Mode is similar to NORM mode but if the AA83 001 is connected as part of a multi unit system the SPLIT mode allows external users to be disconnected from the AA83 001 ICS communications without requiring adjustment of the ICS Audio level All users are permitted to talk to each other listen to music and hear all radio communications There is provision for an external ICS tie line load to maintain the ICS audio at the same level as in NORM mode 910 7 3 FUNCTIONS RADIO FUNCTIONS There are two PTT inputs one each for the pilot and copilot on the control stick Activation of either PTT input connects the user s MIC to the radio and activates the output PTT to the radio Sidetone audio input is provided from the radio not by the AA83 001 microphone circuits Transmit sideline audio utilizes AA83 001 Radio RX audio and phones driver circuits Radio RX sidetone is a mono signal but RX balance control may be adjusted to provide spatial displacement to aid user in quick signal identification NOTE A priority transmission feature allows the pilot to override the copilot MUTING LOGIC When transmitting any m
185. normal or inverted one method always works to stop the spin Power idle Kick rudder to the heavier side this will always be against spin direction Take hands off the stick The spin will end after 1 2 turn The plane will be in a steep dive in a side slip Recovery to normal flight can be performed easily NOTE After six turns of spinning the altitude loss including recovery is 2750 ft 4 13 NOISE CHARACTERISTICS The noise level has been established in accordance with CAO Annex 16 Volume 1 Chapter 10 as 77 7 dB A and FAR 36 Appendix G Amendment 28 pending 4 12 Page Date 6 November 2012 Pilot s Operating Handbook Section 4 EXTRA 300LT XTRA Normal Procedures No determination has been made by the Federal Aviation Administration that the noise levels of this aircraft are or should be acceptable or unacceptable for operation at into oroutof any airport The above noise levels were established at 950 kg 1980 lbs takeoff weight and 2700 RPM This aircraft model is in compliance with all ICAO and FAR 36 noise standards applicable to this type Page Date 6 November 2012 4 13 Section 4 Pilot s Operating Handbook Normal Procedures XTRA EXTRA 300LT Left blank intentionally 4 14 Page Date 6 November 2012 Pilot s Operating Handbook XTRA EXTRA 300LT 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 5 12 5 13 SEC
186. normal polarity injects the smoke oil from the floptube smoke oil tank through an overpressure check valve and the injector nozzle into the hot exhaust gas to generate smoke The system consists of Main smoke oil tank with float switch Floptube smoke oil tank Refill Injection pump in the pilot compartment with quick connector in the belly fairing Overpressure check valve in the smoke oil supply line to the nozzle Filter element in the refill line ON OFF switch on the throttle lever Tworelais changeover contacttype for pump control SMOKE ARM switch to arm the system and SMOKE REFILL switch for refilling placed atthe instrument panel Only 1 circuit breaker for pump and control placed at the instrument panel o 6669 LLL 90 QQ SMOKE SMOKE LANDING ARM REFILL LIGHT 0000000000000 O 15 10 9 o 9 o 9 o H SMOKE LANDING SYSTEM LIGHT o o o o o t 907 6 Page Date 6 April 2010 Pilot s Operating Handbook Section 907 EXTRA 300LT X TRA Smoke System 907 8 HANDLING SERVICING AND MAINTENANCE At every refilling Check automatic shut off Additionally during the 100h Check for the DUAL PUMP SYSTEM Check the system for leakage lines fittings tanks Checkthe smoke oil tanks for proper attachment Checkthe function of the solenoid valve Clean the injector nozzle if required remove carbon debris Additio
187. nsmitter Duetothe better signal integrity ofthe 406 MHz its location accuracy is within abouta 3 km radius 909 2 LIMITATIONS The operation limitations are not effected due to the installation ofthe ARTEX ME 406 ELT Forthe location and operation of the transmitter the following placards have to be attached to the aircraft ELT LOCATED HERE outside on the left fuselage in the vicinity of the ELT unit next to the ELT remote switch gt z o w Kal RI ig z w o x ua z w FOR AVIATION EMERGENCY USE ONLY d R UNAUTHORIZED OPERATION PROHIBITED as close to the ELT remote switch as practical Page Date 6 November 2012 909 3 Section 909 Pilot s Operating Handbook ARTEXME 406 ELT XTRA EXTRA 300LT 909 3 EMERGENCY PROCEDURES ncase of a forced landing turn the remote switch in the rear panel to the ON position prior to touch down Although the ELT will be activated automatically after an aircraft accident or forced landing with high G force turn additionally the remote switch in the rear panel to the ON position After sighting rescue aircraft Switch the remote switch to the ARM position to prevent radio interference e Attempt contact with rescue aircraft with the radio transceiver set to a frequency of 121 5 MHz If no contact is established switch the remote switch to the ON position immediately If the function of the remote switch is in doubt proceed as follows
188. nsmitting a 121 5 MHz distress signal Therefore all activations of the ELT should be keptto a minimum Local or national regulations may limittesting ofthe ELT or impose special requirements or conditions to perform testing For the self test Artex recommends that the ELT be ON for no more than 5 seconds Testing should occur during the first 5 minutes after the hour Page Date 6 April 2010 909 5 Section 909 s Pilot s Operating Handbook ARTEXME 406 ELT XTRA EXTRA 300LT 909 8 HANDLING SERVICING AND MAINTENANCE 909 8 1 TRANSMITTERTEST ARTEX recommends that the ELT be tested every 1 2 months Follow the steps outlined in the 909 8 2 SELF TEST paragraph NOTE The self test time is accumulated in a register on the battery pack The register records activation time in 30 second increments so all activations will count as atleast 30 seconds even if the actual time is much less Total allowable time is 60 minutes as determined by FAR 91 207 and RTCA DO 204 After this time has been accumulated a 7 flash error will be presented after the self test The battery must be replaced at this point for the ELT to remain in compliance Always follow ELT testing requirements per local or national authorities Always perform the tests within the first 5 minutes of the hour Notify any nearby control tower of yourintentions in accordance with AC 43 13 If outside ofthe US alwaysfollow alllocalor national regulations fo
189. nt flight plan leg will be shown in white rather than magenta and a message is presented limiting the RSM GPS to EMERGENCY USE ONLY 917 7 5 OPERATIONONINTERNAL BATTERY NOTE Takeoff with aircraft voltage as indicated on the EFD below 12 3V is not recommended Each EFD1000 or EFD500 is equipped with an internal battery The EFD System incorporates sophisticated power logic to determine when to transition to the internal battery On the ground the system will turn on andturn off with the application or removal of aircraft power In the air the system will transition to battery if aircraft power is removed or degraded Transition thresholds and times will vary as afunction ofthe input voltage to the display which can be observed via the Menu Power Settings Page 917 8 Page Date 6 November 2012 Pilot s Operating Handbook Section 917 EXTRA 300LT XTRA ASPENEFD1000 500 System Battery operation should be expected any time the aircraft charging system is unable to maintain a voltage at the EFD of 12 3 V Under these circumstances should the aircraft dispatch the EFD will transition to battery shortly after reaching flying speed 917 7 6 GEOGRAPHIC RESERVATION NOTE Use ofthe EFD1000 in the region within 750 nautical miles of the magnetic North or South Pole based solely upon the attitude and heading data provided by the EFD1000 is not recommended The ADAHRS solution in the EFD1000 uses multiple inputs including
190. nufactured to related aeronautical specifications 7 13 CABIN ENVIRONMENT CONTROL A ventilation system in the canopy on the left side is provided for the supply of fresh air to the cabin Left and right at the rear seat are eyeball type adjustable vents 7 12 Page Date 6 April 2010 Section 7 Description and Operation of Aircraft and Systems Pilots Operating Handbook EXTRA 300LT XTRA eng DINOIAV OINOIAV VOV Y B Y Joules SNA NIYIN Jexyoos YMS esnJ Jayeeig MOND 14617 Jojeoipu T e e SIE TANG pu 7 aala riv VOL ASVLIOA MO1 ueis 9B1eyo ve ACL junys VO9 AMallvVg LIV8 g dV 6 n Y4Md 1X3 uoivNuariv OS Figure 4 Electrical System 7 18 Page Date 6 April 2010 Section 7 Neu Pilot s Operating Handbook Description and Operation of Aircraft and Systems X TRA EXTRA 300LT 7 14 BAGGAGE COMPARTMENT A baggage compartment is installed behind the pilot s seat in the aft main fuselage cover The compartment may be used only for low density items such as clothes It is limited to a baggage weight of 10 kg 22 lbs The use of baggage is limited to operation in the normal catgegory The compartment consists of a main 7 Figure 5 and a front partition 11 It is accessible by a door 1 from the left aircraft outside The door is hin
191. oll 50ft Roll 50ft Roll 50ft Roll 50ft Roll 50ft Roll 50ft Roll 50ft SL 131 402 143 437 155 475 168 514 181 554 195 597 209 641 2000 610 145 445 158 484 171 526 186 569 200 614 216 661 232 710 4000 1219 161 493 175 537 190 583 206 631 222 681 239 733 257 787 6000 1829 179 547 194 596 211 647 228 700 247 756 265 814 285 874 8000 2438 207 633 225 690 244 748 264 810 285 874 307 941 330 1011 10000 3048 239 732 260 798 282 866 306 937 330 1011 355 1089 382 1169 Weight 870 kg 1918 lbs approach speed 93 KIAS 172 km h OAT gt 20 C A F 10 C 14 O C 32 F 10 C 50 20 C 68 30 C 86 40 C 104 F PA ft m Roll 50ft Roll 50ft Roll 50ft Roll 50ft Roll 50ft Roll 50ft Roll 50ft SL 142 436 155 475 168 516 182 558 197 602 212 648 227 696 2000 610 158 483 172 526 186 571 202 618 218 667 234 718 252 771 4000 1219 175 536 190 583 207 633 224 685 241 740 260 796 279 855 6000 1829 194 595 211 648 229 703 248 761 268 821 288 884 310 950 8000 2438 224 688 244 749 265 813 287 880 310 950 334 1023 358 1098 10000 3048 260 796 283 867 307 941 332 1018 358 1099 386 1183 414 1271 Weight 950 kg 2095 Ibs approach speed 97 KIAS 1
192. orrect Trim SET to appropriate takeoff position half way nose down 4 5 2 TAKE OFF Set throttle smoothly to max and let the airspeed go up to 65 70 KIAS 120 130 km h A light pressure on the stick lifts the tail to horizontal position Rotate the aircraft at 70 KIAS 130 km h On reaching climb speed of 110 KIAS 204 km h proceed with climb Page Date 22 April 2015 4 7 Section 4 Pilot s Operating Handbook Normal Procedures gt XTRA EXTRA 300LT 4 6 CLIMB Climbs may be performed up to 2700 RPM RPM above 2400 should however be used only when necessary for maximum performance in orderto 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 Asrequired 5 Fuel CHECK periodically 4 8 LANDINGPROCEDURES 4 8 1 DESCENT 1 Throttle REDUCE 2 Mixture FULL RICH 3 RPM Control SET to 2400 RPM 4 Trim ADJUST 5 Fuel selector ACRO amp CENTER TANK NOTE Although safe operation does not require the use of the tanks in a specific sequence itis recommended to set fuel selector to ACRO 8 CENTER TANK position 4 8 2 APPROACH 1 Boost pump ON 2 Mixture SET to RICH 3 Airspeed REDUCE to approach speed 4 Propeller SET to low pitch HIGH RPM NOTE lt is recommended to set the RPM to 2400 during approach and landing in order to avoid unnecessary noise In cas
193. ote switch is in doubt proceed as follows Remove quick pins from the backrest adjustment and swivel the backrest forward to get access to the ELT unit Usethe master switch at the ELT unit analogously FUNCTION CHECK OF THEELT e Ifthe aircraft receiver is operable check ELT function by listening on 121 5 MHz for ELT transmission Ensure that the ELT antenna is clear of any obstructions 924 4 NORMAL PROCEDURES It is recommended by the manufacturer to test the ELT to detect any possible failure An operational check must be performed regularly by a pilot or maintenance personnel from the cockpit Remote Control Panel It is recommended to perform a self test once a month but it should not be done more than once a week Each self test consumes energy from the battery Should self tests be carried out more often than the maximum allowed the battery life time might be shorter than specified SELF TESTPROCEDURE e Check that the antenna is correctly connected Do not perform self test without antenna connected Tune aircraft radio to 121 5 MHz and adjust volume to ensure you can hear it 924 4 Page Date 22 April 2015 Pilot s Operating Handbook Section 924 EXTRA 300LT XTRA KANNAD AF 406 ELT e Switch from position OFF to position ARM or press RESET 8 TEST on the Remote Control Panel ensure that the ELT switch is in position ARM Close to the end of the self test a short 3 4 sweeps 121 5 t
194. ould be taken when making routine code changes NOTE When an Aspen EFD1000 PFDis installed itis used as the encoded altitude source Do not power down the Aspen PFD while using the Garmin GTN 635 650 750 unit or the Garmin GTX 33 remote transponder 922 7 5 REMOTE AUDIO PANEL OPERATION GTN 750 ONLY The remote audio panel GMA 35 can be operated from the GTN 750 only It incorporates an intercom functionality The Passenger Address Cabin Speaker Marker Beacon and Telephone functionalities are not used See Figure 5 forthe GTN750 audio panel operation page MIC WINDOW MIC SELECTION 1 Touch the Mic window to toggle between Mic 1 and Mic 2 2 Note that the selected Mic is automatically monitored AUDIO PANEL PAGE MIC SELECTION 1 Touch the Audio Panel key at the top of the display 2 Touch the desired Mic from the MIC Selection list on the right side of the display 922 12 Page Date 6 November 2012 Pilot s Operating Handbook Section 922 EXTRA 300LT XTRA GARMIN GTN 635 650 750 3 The selected Mic will be shown in the MIC window MONITOR 1 Monitor is automatically selected for the associated Com Mic Radio 2 Touch the Mon key to toggle between the automatically selected monitored channel selected Mic and the other available channels Audio Panel Controls Touch to Display Mic Selection 1 or 2 Indicates Additional Audio teo SSUP Source Monitoring NAV com A XPDR NAV com
195. ous digit Pressing the CLR Key when the cursor is on the first digit of the code or pressing the CRSR Key during code entry removes the cursor and cancels data entry restoring the previous code Press the CLR Key up to five seconds after code entry is complete to return the cursor to the fourth digit The numbers 8 and 9 are not used for code entry only for entering a Count Down time and contrast and display brightness IMPORTANT CODES 1200 The VFR code for any altitude in the US Refer to ICAO standards elsewhere 7000 The VFR code commonly used in Europe Refer to ICAO standards 7500 Hijack code Aircraft is subject to unlawful interference 7600 Loss of communications 7700 Emergency 7777 Military interceptor operations Never squawk this code 0000 Military use Not enterable 914 4 Page Date 6 April 2010 Pilot s Operating Handbook Section 914 EXTRA 300LT XTRA GARMIN GTX 328 Transponder Avoid selecting codes 0000 7500 and all codes in the 7600 7777 range These codes trigger special indicators in automated facilities An aircraft s transponder code is used for ATC tracking purposes therefore exercise care when making routine code changes 914 1 3 KEYS FOR OTHER GTX 328 FUNCTIONS IDENT Pressing the IDENT Key activates the Special Position Identification SPI Pulse for 18 seconds identifying your transponder return from others on the air traffic controller s screen The word IDENT will appear in t
196. outlet cooling Gomolzig EA300 606009 32153 shroud 1 Exhaust System 6 in 1 Gomolzig EA300 606000 b 00661 8 48 0 39 A incl Silencer 1 3 inlet outlet cooling Gomolzig EA300 606024 03248 shroud for heating sys Page Date 22 April 2015 6 15 Section 6 Pilot s Operating Handbook Weight and Balance and Equipment List XTRA EXTRA 300LT QTY ITEM MANUFACTURER MODELNO PART NO WEIGHT ARM INST R kg m o A Oil System 79 1 Single Oilcooler rear Aero Classics 31417 1 65 0 22 R 1 Low Temperature 300 Option Breather Line Kit Extra cold weath 0 20 0 01 R Starting 80 1 Starter lightweight Sky Tec 149 12NL 32865 3 65 0 85 R 1 Starter Engaged Light OAK MS25041 4 31732 0 02 1 63 O Other 1 Smoke System Extra 86112 9 20 0 30 O 6 16 Page Date 22 April 2015 Pilot s Operating Handbook XTRA EXTRA 300LT Paragraph 7 1 7 2 7 3 7 4 75 7 5 1 7 5 2 7 5 3 7 5 4 7 5 5 7 6 7 6 1 7 6 2 7 7 7 8 7 9 7 10 7 10 1 7 10 2 7 10 3 7 10 4 7 10 5 7 10 6 7 10 7 7 10 8 7 10 9 7 11 7 12 7 13 7 14 7 15 SECTION 7 DESCPRIPTION amp OPERATION OF AIRCRAFT AND SYSTEMS Table of Contents Page THEAIRCRA Tica ns 7 3 ef 7 3 WINGS iii 7 4 sic Ee 7 4 FLIGHT CONTROL SYSTEM 25 ke iese see ii sege na riada 7 5 Primary Control SM EE 7 5
197. p to 60 degrees bankangle 2 8 2 ACROBATIC FLIGHT The plane is designed for unlimited acrobatics wing tank must be empty Inverted flight maneuvers are limited to max 4 minutes Recommended basic maneuver entry speeds are listed in the following list NOTE This airplane is capable up to 10g maneuvers If acrobatic maneuvers will be performed with a co pilot or passenger the pilot should ensure that the co pilot passenger has been properly briefed on the physiological effects of high g maneuvers This briefing should include accepted muscles straining and breathing techniques to counter the physiological effects of high g maneuvers During the flight the pilot should ensure the co pilot passenger is doing OK Check weight and C G N CAUTION Particular caution must be exercised when performing maneuvers at speeds above VA 160 KIAS 296 km h Large or abrupt control inputs above this speed may impose unacceptably high loads which exceed the structural capability of the aircraft NOTE For acrobatic maneuvers see Section 4 All maneuvers can be performed in upright and inverted flight attitude 6 Page Date 22 April 2015 Pilot s Operating Handbook E Section 2 EXTRA 300LT X TRA Limitations Maneuvers Recommended entry speeds IAS Symbol Remarks min knots km h max knots km h Segment horizontal Line Vs Vue j 45 climbing 80 148 Vue Ba 90 up VA Vue 45 diving Vs V
198. prohibited Smoking is prohibited 2 11 1 STRUCTURAL TEMPERATURE COLOURLIMITATION Structure is qualified up to 72 C 161 6 F Structure temperatures composite above 72 C 161 6F are not permitted Not to exceed this temperature limit color specification for composite structure manufacturer document EA 03205 19 has to be complied with To check the temperature inside the cockpit potential green house effect a reversible temperature indicator STRUCTURAL OVERHEAT INDICATOR is applied on the upper side ofthe wing main spar in the carry through section After reaching the temperature limit of 72 C 161 6 F the word RISK appears and flying is prohibited STRUCTURAL CAUTION While the word OVERHEAT RISK INDICATOR appears flying EXTRA is prohibited 2 12 MAXIMUM OPERATING ALTITUDE Max certified operating altitude is 10 000 ft 3048 m MSL 2 13 TIREPRESSURE The tire pressure is 3 4 bar 49 psi 2 14 MARKINGS AND PLACARDS 2 14 1 AIRCRAFTIDENTIFICATIONPLATE 9 EXTRA 9 o TC NUMBER o FLUGZEUGPRODUKTIONS MODEL EA 300 LT OSERIAL NUMBER O The latest national aviation regulations must be observed in determining whether the placard is required call sign placard 2 8 Page Date 22 April 2015 Pilot s Operating Handbook Section 2 EXTRA 300LT XTRA Limitations 2 14 2 OPERATING PLACARDS Va 160 KTS ACRO Va 296 km h ACRO Va 143 KTS NORMAL o Va 265 km h NORMAL
199. quencing of waypoints Whenever OBS mode is selected you may set the desired course to from a waypoint using the OBS Page or an external OBS selector on your HSI or CDI The message key MSG is used to view system messages and important warnings and requirements 916 6 Page Date 6 April 2010 Pilot s Operating Handbook Section 916 EXTRA 300LT XTRA GARMIN GNC 420W GNS 430W The flight plan key FPL allows you to create edit activate and invert flight plans as well as access approaches departures and arrivals A closest pointto flight plan feature is also available from the flight plan key NOTE Whenever the GNC 420W GNS 430W is displaying a list of information that is too long for the display screen a scroll bar will appear along the right hand side of the display The scroll bar graphically indicates the number of additional items available within the selected category Simply press the small right knob to activate the cursor and turn the large right knob to scroll through the list The procedures key PROC allows youto select and remove approaches departures and arrivals from yourflightplan When using aflight plan available procedures for your departure and or arrival airport are offered automatically Otherwise you may selectthe desired airport then the desired procedure POWERING UP THE GNC 420W GNS 430W The GNC 420W GNS 430W power and COM volume are controlled using the power volume knob atthe top
200. r Seat seat belts w ratchet shoulder harness crotch strap Safety Belt Assy Front Seat seat belts shoulder harness crotch strap Safety Belt Assy Front Seat seat belts w ratchet shoulder harness crotch strap First Aid Pack Electric Trim System Fuel System 28 Elec Fuel Pump Extra Extra Extra Concorde Potter amp Brumfield Bosch Bosch Prestolite Plane Power Electronics Intern Electronics Intern Cole Hersee Extra Sutars Hooker Hooker Hooker Hartmann Ray Allen Weldon Tool RG 25XC 1218 1011230 3x amp 1113012 1 1x 1H5630 3 2x 1CS924 D 1x 1011230 4x 1H3030 3 2x 1CS924 D 1x 1011230 3x amp 1113012 1 1x 1H3030 3 2x 1CS924 D 1x B8120 M 83801 002 01 FB 83401 001 LK Option 300 LT KBS01 03617 03618 FT0001 33508 33558 33552 FA3008 FA3007 PG 31731 02636 31494 FK0002 or FK0019 FKOOO4 or FK0020 33423 31668 01207 0 05 0 25 3 70 10 40 0 05 4 60 4 20 4 00 3 00 0 09 0 22 0 29 0 02 0 03 3 30 2 90 3 30 0 39 0 40 1 10 1 07 1 90 0 20 0 23 1 60 0 86 0 86 0 86 0 86 1 50 1 62 2 33 0 17 1 62 2 12 1 03 1 03 2 70 4 24 0 04 Mooring 10 O O O Electrics 24 m m gt gt D D D o Emergency Equipment R Flight Controls 27 R R Required O Optional A Alterna
201. r altitude temperature and density Va Maneuvering speed Vu Never exceed speed Vue Maximum structural crusing speed Vs Stalling speed or minimum steady flight speed Vx Best angle of climb speed Vy Bestrate of climb speed 1 6 Page Date 6 April 2010 Pilot s Operating Handbook EXTRA 300LT XTRA General Meteorological terminology ISA OAT International standard atmospheric condition Outside airtemperature 1 10 SECONDARY TERMINOLOGY fpm US gal US qt hp kts km h lbs hPa inHg MP PA nm rom CG Arm Moment Feet minute Feet 0 3048 m inch 2 54 cm Meter Litres US liquid gallon 3 79 litres US liquid quart 0 946 litres Horse power english Hour Knots nm h 1 852 kilometer per hour Kilometer per hour English pound 0 4536 kg hekto Pascal Inches of mercury Manifold pressure Pressure altitude ft Nautical miles 1 852 km Revolutions per minute Center of gravity Arm is the horizontal distance from reference datum is the product of weight of an item multiplied by its arm Page Date 6 April 2010 EXTRA 300LT Pilot s Operating Handbook XTRA CONVERSION TABLE Section 1 General 1 11 OD TO NIMH A 00 CO O SF O tO O CO NIH SO DOJO QD O C Om FY CO LO CN Ob C cO TI TININ OO OT LO Lo OIE OO D D O O No CO TP PIB DIN LO mM O 69 OOI TTT LINN NY NI OO OT ST S
202. r movement on the fuel flow gauge During engine start MVP 50P ON 918 5 PERFORMANCE Not affected 918 6 WEIGHT 8 CENTER OF GRAVITY Refer to the equipment list in Section 6 of this Handbook 918 4 Page Date 6 April 2010 Pilot s Operating Handbook Section 918 EXTRA 300LT XTRA ElMVP 50P 918 7 SYSTEMDESCRIPTION The MVP 50P Main Engine Screen displays the primary engine and aircraft instruments This screen is displayed on power up and is the screen that should be monitored for most of the flight ELECTRONICS INTERNATIONAL 2 IR 11 LR Ox FCT TH 00 00 OO F FLOW OL OAT bbe NE 12010 14 01 39 0 Or po US ee oe al S em ECT 66 CHT 66e VOLTS 12 6u DIFF Os DIFF 1er PA Loc Ed SELECT EXIT SCREENS MENU E Figure 1 MVP 50 with Main Engine Screen Buttons operate as follows Push Select Moves the cursor selects functions and changes digits Exit Exits out of a field or screen and returns the display to the Main Engine Screen Screens Switches the display between screens as selected in the Screens Button Setup Menu Displays a menu if available for the current screen To assistthe pilotin identifying the current operating band green yellow red etc the MVP 50P displays the digital value for each function in its appropriate color band When a function reaches aredor yellow operating band blinking digits for that function will alert the pilot To acknowledge the alarm and stop the
203. r testing of ELT s N CAUTION Do not allow test duration to exceed 5 seconds A false alarm may be generated Any time the ELT is activated it is transmitting a 121 5 MHz distress signal After approximately 50 seconds a live 406 MHz distress signal is transmitted and is considered valid by the satellite system Whenever the ELT is switched from ON to ARM a 406 MHz signal is transmitted however itis specially coded as a self test signal that is ignored by the COSPAS SARSAT satellites 909 8 2 SELFTEST Tune areceiver usually the aircraft radio to 121 5 MHz Turnthe ELT aircraft panel switch ON for about 1 second then back to the ARM position The receiver should voice about 3 audio sweeps Atturn off back to ARM state the panel LED should present 1 pulse buzzer will not sound for 1 pulse If more are displayed determine the problem from the list below 1 Flash Indicates that the system is operational and that no error conditions were found 3Flashes Bad load detected Detects open or short condition on the antenna output or cable These problems can probably be fixed by the installer Check that the RF cable is connected and in good condition Perform continuity check of center conductor and shield Check for a shorted cable e Check for intermittent connection in the RF cable 909 6 Page Date 6 April 2010 Pilot s Operating Handbook EXTRA 300LT XTRA ARTEXME 406ELT
204. r to section 1 General Sample Problem Except in 8 5 6 all examples presented in the performance charts refer to the conditions of the sample problem outlined here CONDITIONS Takeoff Weight MTOW 950 kg 2094 Ibs Field Pressure Alt 2000 ft 610 m Temperature 20 C Wind Component Headwind 10KT Field Length 3000 ft Cruise Total Distance 400NM Pressure Altitude 8000 ft 2438 m Temperature ISA 1T Landing Weight 870 kg 1918 lbs Field Pressure Alt 2000 ft 610 m Temperature 10T Wind Component Headwind 5 KT Field Length 2000 ft Page Date 6 April 2010 5 3 Section 5 Pilot s Operating Handbook Performance XTRA EXTRA 300LT TAKE OFF 5 5 shows the Take Off Distance Example T O Weight 950 kg 2095 Ibs Ground Roll 223m 732 ft decreased by 8 due to headwind 205m 673 ft Total Distance to clear a 50 ft obstacle 385 m 1263 ft decreased by 8 due to headwind 354 m 1161 ft These distances are well within the available field length in this sample problem CLIMB 5 6 shows the Rate Of Climb Performance conditions outlined in Fig 5 6 deviate from the sample problem given here Pressure altitude 5000 ft Outside airtemperatur 5 Weight 900 kg 1984 lbs Climb Rate 2104 ft min 5 7 shows the Time Fuel and Distance to Climb Example climb from 2000 ft 610 m to 8000 ft 2438 m Time to Climb 3 52 0 77 min 2 75 min Fuel to Climb 7 63
205. ransmission is made confirm this on the aircraft radio After afew seconds the test result is displayed with the red visual indicator Onelongflash indicates that the system is operational and that no error conditions were found Aseries of short flashes indicates the test has failed Remark The number of flashes gives an indication of the faulty parameter detected during the self test fates kes Low RF Power Fauly VCO Lockhg Fauly Fiequency No Identfraton Programmed If self testfails contactthe distributor as soon as possible Unless a waiveris granted flight should be cancelled 924 5 PERFORMANCE Not affected 924 6 WEIGHT amp CENTER OF GRAVITY Refer to the equipment list in Section 6 of this Handbook 924 7 SYSTEMDESCRIPTION The ELT installation consists ofthe ELT unit fastened to the fuselage structure aft of the back seat an antenna located on the main fuselage cover behind the cockpit and a remote switch with a red visual indicator LED located on the instrument panel The remote switch has the positions ON ARMED and RESET TEST The switch on the ELT unithas the positions ADM OFF and ON Page Date 22 April 2015 924 5 Section 924 SCH Pilot s Operating Handbook KANNAD AF 406 ELT XTRA EXTRA 300LT 924 7 1 SWITCHOPERATION In a crash an acceleration activated crash sensor G switch turns the ELT on automatically Activation is also accomplished by swi
206. rating Handbook EXTRA 300LT 902 7 DESCRIPTION OF THESYSTEM The electrical pedal adjustment system consists of a foot rest and the rudder pedal itself including brake pedal and brake cylinder An S shaped cable leader is attached to the rudder pedal through which the control cable runs from the rudder actuator arm to the front cable attachment at the steel frame The connection to the front seat pedals is realized by a further cable which is fixed to the control cable by two Nicopress oval sleeves The stepless pedal adjustment is realized by electromechanical actuators which are controlled separately by switches on the rear instrument panel refer to Figure 1 below The total travel of the system is limited to 6 3 by a front and a rear stop switch at the slide tube attachment A full travel from the most rearward to the most forward position takes approximately 15 sec 0000000 00000 BACK BACK LEFT RIGHT PEDAL PEDAL r PEDAL ADJUST Figure 1 Switch Circuit Breaker Location 902 8 HANDLING SERVICING AND MAINTENANCE Not affected 902 4 Page Date 6 April 2010 uere EXTRA SECTION 903 CABIN HEATING SYSTEM Table of Contents Paragraph Page 903 1 GENERAL ci 903 3 903 2 LIMITATIONS E 903 3 903 3 EMERGENCY PROCEDURES oue dus 5 vie es kes nt see sku ke ve sedes kes KA be dek kk We de eek Eege NEG 903 3 903 4 NORMAL
207. re TEMPERATURE F 80 40 O 40 80 120 16 15 e O o 14 13 N 12 11 Cr a 10 LU 3 o gt 2 8 7 Cr 6 SS 5 5 C o wd 4 cc a 3 2 1 60 40 20 O 20 40 60 TEMPERATURE C Page Date 6 April 2010 5 5 Section 5 Performance XTRA Pilot s Operating Handbook EXTRA 300LT 5 3 AIRSPEED CALIBRATION ER OER EER EER EER EER ER ER ER A EER ER km h kts 50 60 80 100 120 140 160 180 200 220 111 148 185 222 259 296 333 370 407 CAS NOTE Indicated airspeed assumes zero instrument error Page Date 6 April 2010 Pilot s Operating Handbook EXTRA 300LT XTRA Section 5 Performance 5 4 STALL SPEED CONDITION POWERIDLE FORWARD C G STALL SPEEDS ANGLE OF BANK WEIGHT CATEGORY 0 30 45 60 1g 1 159 1 419 29 kg Ibs KIAS km h KIAS km h KIAS km h KIAS km h 950 NORMAL ACRO III 65 70 77 92 2095 120 130 143 170 870 ACROII 62 67 74 88 1918 115 124 137 163 820 ACROI 60 65 71 85 1808 111 120 131 157 Max altitude loss during stall recovery is approximately 100 ft 30 m Page Date 6 April 2010 Section 5 Performance XTRA Pilot s Operating Handbook EXTRA 300LT 5 5 Power Runway TAKE OFF PERFORMANCE T O Power Concrete NOTE For every 5 kts 9 km h headwind the
208. rewall plane W W1 W2 xc W1 x ie die X X2 Page Date 6 April 2010 Section 6 Pilot s Operating Handbook Weight and Balance and Equipment List XTRA EXTRA 300LT If a new weight is added to the known old weight and CG position the resulting new weight and CG can be obtained by a simple calculation Situation before adding item Wo Xo Airplane weight CG position Wn Xn Weight distance from fire wall of item to add New Weight of airplane and new CG W Wo Wn XG WoxXo Wn x Xn CG position W 6 2 1 Owners Weight and Balance Record Enter below all weight change data from aircraft log book EXTRA300LT SERIAL NUMBER Date Description of Weightchange Running empty modification Added Removed weight Wt kg Arm cm Moment kg cm Wt kg Moment kg cm lbs inch Ibs inch lbs Ibs inch Empty weight asdelivered 6 4 Page Date 31 March 2009 Pilot s Operating Handbook Section 6 EXTRA 300LT XTRA Weight and Balance and Equipment List 6 3 CENTER OF GRAVITY CALCULATION SAMPLE PROBLEM PILOT COPILOT Position Rear Seat Front Seat on Sheet 2 17 7 US GAL kg lbs kg los kg bs 99 218 3 99 218 3 99 218 3 99 218 3 Page Date 6 April 2010 6 5 EXTRA 300LT Pilot s Operating Handbook XTRA CENTER OF
209. ril 2010 E OE Dun taut 22 April 2015 HATU RV clan OS 6 April 2010 Tod O TES n ee 6 April 2010 E TEE 6 November 2012 2 2thru2 5 siseneda raisa 6 April 2010 2 S ala 22 April 2015 prr EEUU 6 April 2010 2 B OE ER ER 22 April 2015 EAS ees aaa ee ee 6 April 2010 2 15thru2 16 6 November 2012 Bel thru 3 8 uos eiie test 6 April 2010 e D AR AE 6 November 2012 A 2ibmu Ap 6 April 2010 LE 22 April 2015 4 8 thru 4 11 6 April 2010 4 12 thru 4 14 6 November 2012 5 1 thru 5 16 6 April 2010 i A E 6 November 2012 5 18 thru 6 9 sssss 6 April 2010 RR EE 6 November 2012 6 11 thru 6 13 18 June 2013 6 14 thru 6 16 22 April 2015 TE EEU TED icti res 6 April 2010 7 6 thru 7 7 ees ees ee ee ee 22 April 2015 1 8 thru 7 9 EEN 6 April 2010 TNO EE 22 April 2015 7 11 thru BA sees 6 April 2010 N EE N 6 November 2012 VPL EE Miura dn 22 April 2015 9 3 thru 9 4 esses 6 April 2010 901 1 thru 907 2 6 April 2010 9018 N RT 18 June 2013 907 4 thru 909 2 6 April 2010 909 3 n 6 November 2012 909 4 thru 916 8 6 April 2010 Fa HE 6 November 2012 917 2thru 917 3 6 April 2010 2 TA EE 6 November 2012 dba 6 April 2010 917 6thru918 6 6 Nove
210. s Deviating from the other control surfaces the spar webs of the surfaces of the elevator is built by CRP On the R H elevator half a trim tab is fitted with two hinges The control surfaces are mounted in spherical bearings exception Trim tab To prevent flutter rudder and elevator are mass balanced The balance weight for the rudder is installed in the rudder tip while the balance weights for the elevator are mounted on the outside elevator tips 7 4 Page Date 6 April 2010 Pilot s Operating Handbook Section 7 EXTRAS300LT X TRA Description and Operation of Aircraft and Systems 7 5 FLIGHT CONTROL SYSTEM 7 5 1 PRIMARY CONTROL SYSTEM The EXTRA 300LT is standard equipped with full dual primary flight controls including conventional stick type control columns and adjustable rudder pedals The primary control surfaces are operated through a direct mechanical linkage 7 5 2 LONGITUDINAL FLIGHT CONTROL SYSTEM The two control columns are interconnected by a torque tube The control movements are from there transferred to the elevator by a push rod 7 5 3 LATERAL FLIGHT CONTROL SYSTEM Push and pull rods are connected by sealed ball bearings from the torque tube to the ailerons The ailerons are statically as well as dynamically balanced dynamically with spades The ailerons are supported by lubricated sealed bearings 7 5 4 DIRECTIONAL FLIGHT CONTROL SYSTEM The dual rudder pedals with brake pedals are electric adjustabl
211. s Pressing the CLR key resets thetimer to the initial value STBY The transponder will not reply to any interrogations GND This page is not active CONTRAST This page is only displayed if manual contrast mode is selected in Configuration Mode Contrast is controlled by the 8 and 9 keys DISPLAY This page is only displayed if manual backlighting mode is selected on Configuration Mode Backlighting is controlled by the 8 and 9 keys 915 1 5 CONFIGURATION MODE The configuration is normally set at time of installation including the unique Mode S aircraft address The configuration Mode should not be used during flight Refer to the GTX 330 pilot s guide PN 190 00207 00 applicable revision you received with yourtransponder 915 1 6 ALTITUDE TRENDINDICATOR When the PRESSURE ALT 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 FAILUREANNUNCIATION If the unit detects an internal failure the screen displays FAIL 915 6 Page Date 6 April 2010 Pilot s Operating Handbook Section 915 EXTRA 300LT XTRA GARMIN GTX 330 Transponder 915 2 LIMITATIONS Notapplicable 915 3 EMERGENCY PROCEDURES 915 3 1 IMPORTANTCODES 7600 Loss of communicat
212. s no ICS music sideline or receive functions NOTE In Automatic Fail safe mode the receive sidetone levels may require adjustment at the audio source The pilot should confirm that all aspects of Automatic Fail safe operation are working before accepting the aircraft into service 910 8 Page Date 6 April 2010 Pilot s Operating Handbook X TRA EXTRA 300LT Paragraph 911 1 911 1 1 911 1 2 911 1 3 911 1 4 911 1 5 911 1 6 911 1 7 911 1 8 911 2 911 3 911 3 1 911 4 911 5 SECTION 911 BECKER ATC 4401 TRANSPONDER Table of Contents Page GENERAL A mE 911 3 Controls and indicators is aiaiai nnne nenne nennen nnns 911 4 Switching on the unit pre flight check 911 4 Squawk selectiOli OR EE RE ER N 911 5 Flight operation in Mode A transponder reply code only 911 7 Flight operation in Mode A C reply code and altitude code ee ee 911 7 So EE EE ER N 911 7 MEE EA OR a MA OE AO 911 7 Configuration de EE 911 8 RE dle OE ER EE OE SL 911 8 EMERGENCY PROCEDURES cocinan 911 8 Important CodeS zouen isein anaana ae Aae ET 911 8 NORMAL PROCEDURES eege 911 8 PERFORMANCE ti 911 8 Page Date 6 April 2010 911 1 Section 911 Pilot s Operating Handbook BECKER ATC 4401 Transponder XTRA EXTRA 300LT Left blank intentionally 911 2 Page Date 6 April 2010 Pilot s Operating Handbook Section 911 EXTRA 300LT XTRA BEC
213. se information can also be accessed via the main menu Page Date 6 November 2012 917 7 Section 917 Pilot s Operating Handbook ASPEN EFD1000 500 System XTRA EXTRA 300LT Database Provider High resolution terrain data for Americas i Jeppesen International or Worldwide geographic regions mail order Terrain depiction is limited to the region between 65 deg N orth latitude to 65 deg South latitude Includes Navaids Controlled Airspace Restricted Jeppesen Prohibited and Special Use Airspace Airports etc JSUM These databases Includes Roads Rivers Railroads Political Jeppesen 8 boundaries Cities etc JSUM intended to improve flight crew Includes man made obstacles greater than 200 ft Jeppesen awareness AGL This database relies upon data reported by JSUM and are not government agencies and may not include all to be used obstacles due to inherent reporting and processing for delays in the data In addition obstacle data may navigation not be available for all regions within the data card coverage area NACO Terminal Procedures Charts 917 7 4 RSMGPSUSAGE The EFD1000 500 System includes a non certified GPS receiver This GPS can provide positioning data when all other approved sources of GPS data have failed Position data from the RSM GPS will only become available for use following a loss of position information from all other connected GPS system s When the RSM GPS is in use the curre
214. sponsible forterrain and obstacle avoidance by visual means At system start up the pilot must acknowledge this operational limitation by pressing either MODE SYNC knob Evolution Synthetic Vision is acomputer generated image ofthe external scene topography from the perspective of the flight deck derived from aircraft altitude high precision navigation solution and database of terrain obstacles and cultural features such as runways Evolution Synthetic Vision creates an image relative to terrain obstacles and airports within the limits ofthe navigation source altimetry and databases Evolution Synthetic Vision provides situation awareness butno operational credit The intended function is flight crew awareness ofthe external scene topography The Aspen Evolution Synthetic Vision System uses 9 arc second resolution data enhanced with 3 arcsecond data to provide better depiction of the terrain The depiction of terrain is most like the outside view in the narrow FOV1 view and a more expansive view of the horizonis available in FOV2 The terrain depicted in FOV2 is closer than it appears The intended function of the Flight Path Marker is to display the current vertical and lateral path of the aircraft based on two parameters barometric vertical speed and GPS track These parameters lag during dynamic maneuvers Therefore the Flight Path Marker should only be used during steady state nonaccelerated flight It is not intended to provide accurate i
215. ssie see es De a GE 4 9 4 11 B zd caas zE illie ga 4 9 4 12 ACROBATIC MANEUVERS occiso 4 10 4 12 1 ear 4 10 4 12 2 MANGUVORS E 4 10 4 12 3 em TED 4 12 4 13 NOISE CHARACTERISTICS E 4 12 Page Date 6 November 2012 4 1 Section 4 Pilot s Operating Handbook Normal Procedures XTRA EXTRA 300LT Left blank intentionally 4 2 Page Date 6 April 2010 Pilot s Operating Handbook XTRA Section 4 EXTRA 300LT Normal Procedures 4 0 GENERAL 4 0 1 AIRSPEEDS FOR NORMAL OPERATION 4 0 2 CATEGORY ACROI ACRO II ACROIII NORMAL 820 kg 870 kg 950 kg 950 kg 1808 lbs 1918 lbs 2095lbs 2095 lbs KIAS km h KIAS km h KIAS km h KIAS km h Start Rotate Speed 65 120 67 124 70 130 70 130 Climb Vx 70 130 72 133 75 139 75 139 Vy 88 163 91 169 95 176 95 176 Recommended Normal Climb Speed 100 185 105 194 110 204 110 204 Max Cruise 205 380 205 380 205 380 205 380 Landing Approach 90 167 93 172 97 180 97 180 onFinal 79 146 81 150 85 157 85 157 Go Around Speed 102 189 105 194 110 204 110 204 Recommended Airspeed For Flight In Rough Air max Va 160 296 160 296 160 296 143 265 Max Demonstrated Cross Wind Component 15kts 27 15kts 27 15kts 27 15 kts 27 CHECKLIST AND PROCEDURES This handbook contains the checklist and procedures to operate the aircraft in normal a
216. t Number 0010017605 d Page Date 31 May 2012 921 1 Section 921 Pilot s Operating Handbook AIRPLANES REGISTERED IN BRAZIL XTRA EXTRA 300LT Left blank intentionally 921 2 Page Date 31 May 2012 Pilot s Operating Handbook Section 921 EXTRA 300LT XTRA AIRPLANES REGISTERED IN BRAZIL 921 1 GENERAL This supplement is approved by the EASA on behalf of the Ag ncia Nacional de Aviagao Civil ANAC for Brazilian registered aircraft in accordance with the Regulamento Brasileiro da Aviagao Civil RBAC 21 Section 21 29 Theinformation contained within this supplementis to be used in conjunction with the basic AFM POH and supplements The information contained herein supplements or supersedes that in the basic manual and approved supplements only in those areas indicated Thefollowing POH AFM supplements are ANAC approved Section Title 901 Steerable Tail Wheel 902 Electric Pedal Adjustment 903 Cabin Heating System 904 Accelerometer TL 3424 EXT 905 External Power 906 Digital RPM Indicator 907 Smoke System 908 Single Seat Canopy 909 ARTEXME 406 ELT 910 NAT AA83 001 Intercom 911 BECKER ATC 4401 Transponder 912 BECKER BXP 6401 Transponder 913 GARMIN GTX 327 Transponder 914 GARMIN GTX 328 Transponder 915 GARMIN GTX 330 Transponder 916 GARMIN GNC 420W GNS 430W 917 ASPEN EFD1000 500 System 918 EI MVP 50P Compliance with the limitations contained in the basic manual
217. t s Operating Handbook GARMIN GNC 420W GNS 430W XTRA EXTRA 300LT Left blank intentionally 916 2 Page Date 6 April 2010 Pilot s Operating Handbook Section 916 EXTRA 300LT XTRA GARMIN GNC 420W GNS 430W 916 1 GENERAL The Garmin GNC 420W GNS 430W GPS Navigator is a panel mounted unit that contains a GPS receiver for GPS navigation plus VHF Com radio in an integrated unit with a moving map and color display The GNC 420W GNS 430W features a graphical display which may also be usedto depict terrain data The GNS 430W also features NAV functionality Photocell for Auto Dimmin Com Freq Graphic Moving Comm Pad Window Map Display and Direct To Key Flip Flop nd Navigation Info Range Keys Menu Key Power and Com Clear Key Data Cards 3 Er 9 WRO 1 Tx gt Enter Key h rmm d Function and Nav Radio Page Number Volume Nav Radio eee LE Fa Large Knob Flip Flop RS INAV ost CARR Large Knob ER TOR Me ARE PROD Small Knob Com VLOC Nit Cursor Press Freq MHz Terrain Flight to activate Small Knob Phase and Flight Plan Com VLOC GPS Integrity i Procedure Key Freq kHz Annunciator ee cr Navigation Source GPS VLOC or GPS PTK This supplementis written for main software version 3 00 and GPS software version 3 0 andis not suitable for earlier software versions Some differences in operation may be observed when comparing the information in this supplement to la
218. tching the cockpit mounted remote switch or the switch on the ELT to the ON position To deactivate the ELT switch the switch on the ELT unit to the OFF position NOTE With remote switch disconnected or during transport the ELT can still be manually activated using the local switch on the front of the ELT Care should be taken when transporting or shipping the ELT not to move the switch or allow packing material to become lodged such as to toggle the switch It is possible to stop the ELT in case of unintentional activation Switch to OFF Regulations state that no transmission must be interrupted unless all means are used to contact and inform the Air Traffic Controller of this action NOTE As 406 MHz transmission is effective 50 seconds after the ELT activation if itis switched off within this delay no further radio contact will be necessary 924 8 HANDLING SERVICING AND MAINTENANCE Refer to the following applicable manufacturer instructions for further detailed information or when working on the Kannad 406 AF ELT Installation and Operation Manual 406 AF COMPACT ELT P N DOCO8038E Rev 04 e Initial Installation Manual 406 AF INTEGRA ELT P N DOCO9081C Rev 02 e Operation Manual 406 AF INTEGRA ELT P N DOC09078C Rev 02 Manufacturer Kannad Aviation McMurdo Group Orolia SAS Z l des 5 Chemins BP 23 56520 Guidel F 924 8 1 PERIODICINSPECTION Depending ifthe ELT is openedor not PART 145 or FAR 145 or equivalent may b
219. ter software versions Verify the information herein with the 400W Series Pilot s Guide amp Reference P N 190 00356 00 applicable Revision you received with your unit There you will also find further information 916 2 LIMITATIONS The system must utilize main software version 3 00 and GPS software version 3 0 or later FAA approved versions A valid and compatible database must be installed and contain current data The information provided by the GNC 420W GNS 430W is for situational awareness only and should notbe relied upon for navigation Page Date 6 April 2010 916 3 Section 916 R Pilot s Operating Handbook GARMIN GNC 420W GNS 430W XTRA EXTRA 300LT 916 2 1 PLACARDS GARMIN GPS limited to VFR use only In the clear view of the pilot GPS Next to the GNC 420W GNS 430W circuit breaker 916 3 EMERGENCY ABNORMAL PROCEDURES 916 3 1 EMERGENCY PROCEDURES Not affected 916 3 2 ABNORMALPROCEDURES GPS NAVIGATION INFORMATION NOT AVAILABLE OR INVALID If GNC 420W GNS 430W GPS navigation information is not available or invalid utilize remaining operational navigation equipment as appropriate LOSS OFINTEGRITY MONITORING If Loss of Integrity Monitoring message is displayed revert to an alternate means of navigation appropriate to the route and phase of flight or periodically cross checkthe GPS guidance to other approved means of navigation LOSS OF GPS SIGNAL DURING ACROBATICS When performing a
220. the Aspen PFD MFD is for situational awareness only and should not be relied upon for navigation The aircraft ownship position presented on the Airport Diagrams may be inaccurate reference to the ownship position for navigation or maneuvering is prohibited 917 2 1 PLACARDS AND DECALS PFD Next to the EFD PFD System circuit breaker MFD Next to the EFD MFD System circuit breaker dT ENE IE TENK INA above the EFD display head s 917 4 Page Date 6 November 2012 Section 917 ASPEN EFD1000 500 System Pilot s Operating Handbook EXTRA 300LT XTRA JBAISIBY SdD UHM elNPOIN Josues ejouJ8s SAD INS SINPOIN JOSUSS JOWD Y WSH einpojN UOREANBYUOD ND 80JNOS Sd9 euJa x3 NSH xSd9 NSH i ddd LOlld euondo 0001 043 jeuondo JO CAIN ddd Od Q3IN 0001 dd gt gt 0001 43 00S ddd m m A A A 7 v Y NO NO WO eur JON UE au ONES YEIONY J MOd UEIOIN Figure 1 Equipment Configuration 917 5 Page Date 6 April 2010 Section 917 Pilot s Operating Handbook ASPEN EFD1000 500 System XTRA EXTRA 300LT 917 3 EMERGENCY PROCEDURES Not affected due to the use as a secondary instrument 917 4 NORMALPROCEDURES Not affected due to the use as a secondary instrument
221. the basis for maneuvering and must not be used for navigation 917 10 Page Date 6 November 2012 Pilot s Operating Handbook Section 917 EXTRA 300LT XTRA ASPENEFD1000 500 System 917 7 8 EVOLUTIONSYNTHETIC VISION OPTIONAL NOTE Navigation or maneuvering based solely on the EFD1000 or MFD500 Synthetic Vision background display and associated Terrain Warning System TWS is notauthorized The Pilot in command has the responsibility to use accepted visual procedures to avoid terrain and other obstacles NOTE Flight with an expired database is not recommended An expired database does not prevent terrain or other Synthetic Vision features from being displayed NOTE No Sonalertinstalled Only on screen Alert Annunciations FPM Alert Colors and Terrain Coloring are configured The EFD1000 500 Evolution Synthetic Vision system provides a computer derived view of the nearby terrain obstacles and airports The Flight Path Marker graphically presents the aircraft vertical speed and the GPS track converted to an angular direction The Terrain Warning System TWS usesthe Flight Path Markerto presentan estimated time to collision function forterrain and obstacles combined with aterrain proximity view that colorizes nearby terrain based on the relative aircraft height Unless inhibited by the pilot TWS even operates when SV is turned off The EFD100 500 display of Synthetic Vision information is advisory only The pilotis re
222. tionally a remote transponder GTX 33 can be controlled viathe GTN 635 650 750 unit Touch the transponder window to enter the trnasponder operation page See figures 3 and 4 for the GTN 6xx and the GTN 750 respectively IDENT 1 Touch the IDENT key once to reply with an identifying squawk code 2 The IDENT key text will change to green to indicate active Ident 922 10 Page Date 6 November 2012 Pilot s Operating Handbook Section 922 EXTRA 300LT XTRA GARMIN GTN 635 650 750 STANDBY 1 Touch the Mode key to show a list of available modes directly accessible from the transponder operation page on the GTN 750 Touch the Standby key to place the transponder into Standby mode The transponder will still be powered but will not transmit information The active transponder indication and Ident annunciation will be grayed to show they are disabled GROUND 1 Touch the Ground key to place the transponder into Ground mode Mode S replies will be allowed in Ground mode ON 1 Touch the On key for Mode A operation The transponder is On and will transmit its squawk code when interrogated ALTITUDE REPORTING 1 Touch the Altitude Reporting key for Mode C operation 2 The transponder will be On and will transmit its squawk code and altitude when interrogated An ALT annunciation will appear when the squawk code is transmitted VFR 1 Touch the VFR key to set the VFR squawk code 1200 or 7000 dependin
223. tive Page Date 6 November 2012 Pilot s Operating Handbook XTRA Section 6 EXTRA 300LT Weight and Balance and Equipment List QTY ITEM MANUFACTURER MODELNO PART NO WEIGHT ARM INST R kg m O A 1 Elec Fuel Pump Andair PX580 TC XT 33551 0 47 0 04 A 1 Fuel Selector Allen 390144 0 19 0 73 R FuelLines in Fuselage Parker Stratoflex 33315 1 65 0 70 R 1 Fuel Cont Probe Wing VDO FM4006 0 12 0 89 R 1 Fuel Cont Probe Wing VDO FM4006 0 12 0 89 O 1 Fuel Cont Probe Fuselage Tank VDO 01920 0 20 0 44 R Landing Gear 32 2 Main Wheel Tires Goodyear McCreary 5 00 5 6PR 02323 3 90 0 33 R 2 Tube div FF0016 3 90 0 33 R 2 Wheel assembly Cleveland 02497 6 40 0 33 R 2 Master Brake Cyl front Matco FB0001 0 55 0 15 R 2 Master Brake Cyl rear Matco FB0001 0 55 1 15 R 1 Tail Wheel 6 Assy Special Products Soft Aviation Inc 32477 VB 1 28 5 23 1 Tail Wheel 5 Extra 125 50 75ZL 53201 007 VB 0 90 5 23 1 Wheel fairing LH CFRP Extra 5D102 301 01 LV 1 11 0 33 O 1 Wheel fairing RH CFRP Extra 5D102 301 02 LV 1 11 0 33 1 Brake Fluid Reservoir ACS 02889 0 20 0 04 R 4 4 4 Strobe Nav Light RH Strobe Nav Light LH Strobe Power Supply Landing Light Landing Light LED Navigation Flight Instruments Avionics Accelerometer 3 1 8 Accelerometer 2 1 4 Whelen Whelen Whelen Xevision Whelen Kollsman or Pioneer or Bendix or Jaeger
224. to 7 Ident push button IDT In Mode A and Mode A C this triggers the transmission of an identification impulse additional to the Mode A reply code for approx 18 seconds During this time H appears in the bottom line of the LC display 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 On appears in the display IDT is displayed the duration of the identification function Mode A C ALT 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 ldt is displayed for the duration of the identification function Code push button Activates a first user specific VFR code VFR1 Code push button Activates a second user specific VFR code VFR2 Reply indication The triangle signals a Transponder reply REPLY Store push button Stores user specific VFR codes or changes in STO the configuration mode 911 1 2 SWITCHING ONTHE UNIT PRE FLIGHT CHECK 1 Checkthat the circuit breaker is set and switch on the aircraft power supply YN CAUTION Do not switch on the transponder ifthe motors or engines are being started or shut down 2 Using mode switch A switch the transponder
225. torage 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 Activation of the VFR codes Press the VFR push button 1 or 2 F G The selected code is then displayed After 3 seconds the displayed code becomes activate and overwrites the previously set reply code Pressing button F or G again within 3 seconds reactivates the previously set reply code NOTE When the unit is delivered the store buttons are not assigned a code This means that if these buttons are pressed for 0 5 seconds is shown in the code display and the transponder then switches back to the previously active code IMPORTANT CODES 1200 The VFR code for any altitude in the US Refer to ICAO standards elsewhere 7000 The VFR code commonly used in Europe Refer to ICAO standards 0021 The VFR code commonly used in Germany default is set to 0021 at time of installation 7500 Hijack code Aircraft is subject to unlawful interference 7600 Loss of communications 7700 Emergency 7777 Military interceptor operations Never squawk this code 0000 Military use Not enterable 911 6 Page Date 6 April 2010 Pilot s Operating Handboo
226. trap All belts are adjustable As each lap belt features a single point release they are redundant for safety during aerobatic maneuvers If one release is opened unintentionally the second one guarantees full safety For safe operation the releases are arranged in a way that one has to be closed to the right side the other one to the left During acrobatic maneuvers the seat belt system should be tightened firmly 7 9 CANOPY The canopy is manufactured in one section and can be manually operated by interior locking handles located on the left side on the canopy To open the canopy from inside proceed as follows Pull together the interior locking handles of the front or rear seat and lift canopy to the right The canopy strap will limit the opening angle To lock the canopy pull together the interior locking handles and then release To open the canopy from the outside use the aft interior handles by reaching through the small window bad weather window and proceed as mentioned above Generally the emergency operation is equal to the normal procedure When opening the canopy in normal flight the low pressure over the canopy will flip the canopy fully open immediately However complete jettison of the canopy is possible In this case the canopy can be finally unlatched at its RH hinge line by the following action push canopy slightly forward while opening 7 8 Page Date 6 April 2010 Pilot s Operating Handbook Section 7 EXTRA
227. tronik TL 3424_EXT 32582 0 30 1 60 O audio visual warning Avionics 34 amp 23 1 VHF Com Becker AR 4201 00652 PG 0 67 1 54 R 1 VHF Com Becker AR 6201 33041 0 85 1 54 8 33kHz ch spacing 1 VHF Com Funkwerk ATR 833 32363 0 60 1 55 A 8 33kHz ch spacing 1 GPS COM Garmin GNC 420W 32734 PG 2 65 1 54 O 1 GPS NAV COM Garmin GNS 430W 32773 PG 2 95 1 54 A 1 GPS NAV COM Garmin GNS 530W 28219 PG 3 75 1 49 A 1 GPS COM Garmin GTN 635 33772 PG 2 82 1 54 A 1 GPS NAV COM Garmin GTN 650 33773 PG 3 20 1 54 A 1 GPS NAV COM Garmin GTN 750 33774 PG 4 24 1 54 A 1 COM Antenna Pointer P1 3001 10 FE4254 0 05 4 38 R 1 GPS Antenna Garmin GA 35 32620 0 21 3 90 O 1 NAV Antenna Comant Industries Cl 158C 33035 0 16 3 90 O 1 Diplexer Comant Industries CI 507 FA4057 0 09 3 90 O 1 Course Deviation Ind Garmin Mid Continent GI 102A FA3010 0 64 1 54 O 1 Course Deviation Ind GS Garmin Mid Continent GI 106A FA3003 0 64 1 54 O 1 Transponder Mode S Becker BXP6401 2 01 31860 PG 0 80 1 60 O 1 Transp Mode A amp C Garmin GTX 327 FA3009 PG 0 95 1 75 O 1 Transponder Mode S Garmin GTX 328 32839 PG 1 50 1 73 O 1 Transponder Mode S Garmin GTX 330 30334 PG 1 50 1 73 O 1 Transponder Mode S Garmin GTX 33 33775 PG 2 00 3 02 O 1 Transp mode A amp C Becker ATC 4401 31002 PG 0 73 1 60 O 1 Blind Encoder Module Becker BE 6400 01 32100 1 10 1 39 O 1 Altitude Blind Encoder ACK A 30 02239 0 20 1 50 O 1 Altitude Bl
228. ttery switch ON 14 Pull the external power plug from the board receptacle 905 5 PERFORMANCE Not affected 905 6 WEIGHT AND BALANCE Refer to the Equipment List in Section 6 of this Handbook 905 7 DESCRIPTION OF THE SYSTEM The external power receptacle with its spring loaded door is attached left under the seat and reachable from outside It is directly connected to the aircraft electrical system and does not feature an inverse polarity protection refer to Fig 7 4 So it is advisable to check correct polarity of the external power plug During the engine start the battery switch has to be switched in OFF position for the disconnection of the battery from the aircraft electric circuit 905 8 HANDLING SERVICING AND MAINTENANCE Not affected 905 4 Page Date 6 April 2010 uere EXTRA SECTION 906 DIGITAL RPM INDICATOR Table of Contents Paragraph Page 906 1 GENERAL 2 906 3 906 2 M rye E 906 3 906 3 EMERGENCY PROCEDURES 1 5 seek vie es kes nt et ee sku ke ve sedes kes ri 906 3 906 4 NORMAL PROCEDURES 51 5 i 906 3 906 5 dde i sc 906 3 906 6 WEIGHT AND BALANCE neon dida 906 3 906 7 DESCRIPTION AND OPERATION OF THE SYSTEM see see ee ee ee ee ee nen 906 3 906 8 HANDLING SERVICING AND MAINTENANCE ese ee ee serene ee ee nennen nnne 906 5 Page Date 6 April 2010 Section 906
229. uch Continue 922 7 7 MAPPAGE During most flights the Map page will be used for situational awareness The Map page displays Airports NAVAIDs airspace airways land data highways cities lakes rivers borders etc with names wind direction and speed icons for enabled map features aircraft icon with the nose representing present position nav range ring flight plan legs a graphic course deviation indicator CDI with From To Next waypoints topography scale terrain overlay The Map page is reached by touching the MAP key on the Home page or by pressing and holding the Home key 922 7 8 GROUND OPERATION NOTE Do not use SafeTaxi or Chartview functions as the basis for ground maneuvering SafeTaxi and Chartview functions are not qualified to be used as an airport moving map display AMMD SafeTaxiand Chartview are to be used by the flight crew to orient themselves on the airport surface to improve pilot situational awarness during ground operations 922 7 9 TRAFFIC DISPLAY OPTIONAL Traffic may be displayed on the GTN when connected to an approved TIS traffic device e g GTX 330 or GTX 33 The TIS information is only available in the US The Garmin GTN 6xx or 7xx Cockpit Reference Guide or Pilot s Guide provides additional information regarding the functionality of the traffic device The display of traffic is an aid to visual acquisition and may not be utilized solely for aircraft maneuvering 922 8 SCREENCL
230. ueunpu3 VER 00 y OC 00 097 007 DCL 0 0001 I 06 i 0002 l T 000 1 AGL 0007 0008 69 E y E 0009 GS 2 St T 000 La 0006 00001 U 6c eoueinpu3 lt Jamo 9 59 000LL 2 L eunjejeduie Ip apising 00021 HV sseug Wgepz H 0008 oan ejdurex3 000 ewod Gy Je uiu Gp JO amasa BI e Joy 1e6 sn 28 T 000 7 seet xe pue dn uue Joy lef sn 1 16 seet ef sn z 99 1607 ent 1830 00081 dl 7602 056 ue suonipuo 00091 0008 J epminiv ysusg 5 Sameiedwe ay apisimo OP 0 Oc OL 0 0L 0c UC Or R N S T S S N Co SS S X EN P ISA 5 13 Page Date 6 April 2010 EXTRA 300LT Pilot s Operating Handbook XTRA CRUISESPEEDS Section 5 Performance 5 10 SVLy pasds asinig D aunyesodwiay ay 9pismo OLZ SOZ 007 S6 06L S9L 08L GIL DL S9L 09L SSL OSL Srl OYL SEL OEL SZI Op Oe OZ OL 0 OL OZ 0 OF T 0 AJ In GE BEES W W OZE s ELL peeds sing lt 9901 I J MOd 99 P 9 eunjejeduiej re apisMOL 000Z 06 IV sseJg wggpz Y 0008 esinio SES 000 a H 0007 GL 9669 GG der 1
231. usic will be muted quickly and will slowly return when transmission is completed Music will also be muted when ICS or RX functions are active The degree of muting is set at the time of installation Page Date 6 April 2010 910 7 Section 910 2 Pilot s Operating Handbook NAT AA83 001 Intercom XTRA EXTRA 300LT The relative volume of the music can be changed from the panel by the knob marked with a musical note Below is a simple chart to aid in understanding audio switching in the NORMAL Operation mode we oem o o9 es o9 tes Muted ae ge f We f we function The following terms are used Active Function being used Muted Functions that are overridden by the active condition Idle Functions that are not active but still available for use AUTOMATICFAIL SAFE In the event of a power failure automatic fail safe operation will be activated lt can also be enabled by pulling the AA83 001 circuit breaker Fail safe mode routes the pilot s phones mic audio and mic PTT directly to the COM radio During transmit mode the pilot mic is directly connected to the transceiver mic Mic bias is provided by the transceiver not the AA83 001 The pilot TX keyline is directly connected to the transceiver The sidetone audio is directly connected from the audio source to the pilot phones During receive mode receive audio is directly connected from the audio source to the pilot phones In both modes The copilot ha
232. ust 2007 904 5 Section 904 Pilot s Operating Handbook Accelerometer TL 3424 EXT X TRA EXTRA 300LT SYMBOLS Thefollowing symbols are used inthe TL 3424 EXT display Display Symbol Meaning gt recording to memory I Recording paused ACC Acceleration values indicated up downarrows storing expected release buttons when setting arrows vanish CONTROLLING THEINSTRUMENT VIA NAV MENU There are black labels on the display Each is affiliated to the left and the right button The left label is for the Left button The right label is for the Right button Before pressing a button read the information on the label Its functions are different in every menu To store a value into the memory press both buttons simultaneously Release buttons when the setting arrows vanish SETTING THE DISPLAY BRIGHTNESS Press and hold both buttons while switching on the TL 3424 to enter the setup Followthe menu navigation 904 6 Page Date 6 April 2010 deem EXTRA SECTION 905 EXTERNAL POWER Table of Contents Paragraph Page 905 1 GENERAL Aau 905 3 905 2 LIMITATIONS 2 905 3 905 3 EMERGENCY PROCEDURES 12122 122 2i ee ene sini kass ssds nand sna a a alann sinun aa ek ERG ER Ge sana snam ana 905 3 905 4 NORMAL PROCEDURES 212 222 32022 doenn sae ane ees ese EER AE See gs ee
233. ust be carried in the aircraft as required by the applicable operating regulations NOTE The aircraft ownship position presented on the Airport Diagrams may be inaccurate reference to the ownship position for navigation or maneuvering is prohibited The intended function of Aerodrome Moving Map Display AMMD is to help flight crew orient themselves on the airport surface and improve pilot positional awareness during taxi operations AMMD function is not sufficientto be used as the basis for maneuvering and shall not be used for navigation This application is limited to ground operations only The intersection ofthe wings and fuselage of the aircraftownship symbol onthe AMMD corresponds to the ownship s actual position NOTE The Terminal Procedures Charts depictions on the EFD are not substitutes for aeronautical charts required to be carried aboard the aircraft This function does notreplace any system or equipment required by the regulations The aircraft ownship position presented on the Terminal Procedures Charts may be inaccurately portrayed due to errors in the charts reference to the ownship position for navigation or maneuvering is prohibited The intended function of the Terminal Procedures Charts depiction without the aircraft ownship depicted onthe chart is to provide a convenient location to view portions ofthe Terminal Procedures Charts information The Terminal Procedures Charts depiction is not sufficient to be used as
234. uts from either portable or fixed entertainment systems to produce high quality stereo headset output The stereo music audio is muted during transmit or intercom operation and when receive audio is detected permitting greater intelligibility of incoming transmissions The AA83 001 muting depth adjustment ranges from complete music muting to gentle background music on command with a fast attack and slow level return for optimum user comfort Each microphone is individually gated for the best possible noise performance during VOX operation A panel annunciator allows easy visual setting ofthe VOXthreshold and also indicates transmit operation The AA83 001 provides full boom mic transmit and ICS functions for the pilot and copilot Pilot priority on transmit and pilot isolation fail safe direct connection to the aircraft radio system are standard features YN CAUTION Ensure headsets are of good quality and are installed correctly NEVER USE MONO AIRCRAFT HEADSETS in this system unless the installation has been specifically wired for mono operation as they will short cut one side of the AA83 001 power amplifier when installed in stereo jacks This may result in eventual unit failure which IS NOT COVERED BY WARRANTY Use only stereo headsets with this system INSTALLATION ADJUSTMENTS Using individual level trimpots an approved dealer can adjust the following audio levels during service or at the time of installation Music mute level
235. y disconnected CPD can result in progressively worse effects Page Date 6 April 2010 3 3 Section 3 Pilot s Operating Handbook Emergency Procedures X TRA EXTRA 300LT 3 1 AIRSPEEDS FOR EMERGENCY OPERATION Stall speed 65 KIAS 120 km h Engine failure after take off 85 KIAS 157 km h Best recommended gliding speed glide angle 1 6 2 Normal amp Acro Ill Category 950 kg 2095 Ibs 90 KIAS 167 km h Acro II 870 kg 1918 lbs 87 KIAS 161 km h Acro 820 kg 1808 lbs 85 KIAS 157 km h Precautionary landing with engine power 85 KIAS 157 km h Landing without engine power 85 KIAS 157 km h Maximum demonstrated cross wind component 15 Knots 27 km h 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 Battery switch OFF 6 Alternator switch OFF 3 2 2 ENGINE FAILURE IMMEDIATELY AFTER TAKE OFF Stall speed 65 KIAS 120 km h 1 Airspeed 85 KIAS 157 km h 2 Mixture IDLE CUT OFF 3 Fuel shutoff valve OFF Pull amp Turn 4 Ignition switch OFF 5 Battery switch OFF 6 Alternator switch OFF 7 Forcedlanding PERFORM as practical 3 2 3 ENGINE FAILURE DURING FLIGHT RESTART PROCESS 1 Airspeed 85 KIAS 157 km h 2 Fuel shutoff valve CENTER amp ACRO 3 Mixture RICH 4 Boost pump ON 5 Ignition switch BOTH or START if propeller has stopped 3 4 Page Date 6 April 2010

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