Home

U.S. Version [Last Updated on: Jun 13th, 2014]

1. Page Date 19 February 2014 6 13 Section 6 Pilot s Operating Handbook US Weight and Balance and Equipment List EXTRA 330LX QTY ITEM MANUFACT MODELNO PARTORP N WEIGHT ARM INST kg m 1 Diplexer Comant Industries 1507 4057 0 09 3 90 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 003 0 64 1 54 1 Transponder Mode S Becker 6401 2 01 31860 PG 0 80 1 60 O 1 Transp Mode A amp C Garmin GTX 327 FA3009 PG 0 95 1 75 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 grey code 1 Altitude Blind Encoder ACK A 30 8 or higher 32960 0 20 1 50 O serial output 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 Including ELT Antenna Artex or 110 773 33524 0 08 3 00 Rami AV 200 33965 0 08 3 00 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
2. 5 11 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 OAT 0 32 F 15 C 59 F 30 C 86 F Landing Airspeed PA Land Land Land Land Land Land weight Roll over Roll over Roll over 15m 50 ft 15m 50 ft 15m 50 ft kg KIAS ft m m ft m ft m ft m ft m ft m ft Ibs km h 950 93 SL 171 561 527 1729 177 581 548 1798 185 607 586 1923 2095 172 2000 610 181 594 558 1831 188 617 580 1903 197 646 602 1975 4000 1219 192 630 592 1942 199 653 615 2018 208 682 639 2096 6000 1829 203 666 627 2057 211 692 652 2139 220 722 678 2224 870 89 SL 158 518 488 1601 164 538 507 1663 171 561 527 1729 1918 165 2000 610 165 541 518 1699 175 574 537 1762 181 594 558 1831 4000 1219 177 581 548 1798 185 607 570 1870 192 630 592 1942 6000 1829 188 617 582 1909 195 640 605 1985 203 666 627 2057 820 84 SL 150 492 465 1526 156 512 483 1585 163 535 502 1647 1809 156 2000 610 159 522 492 1614 166 545 511 1677 173 568 532 1745 4000 1219 168 551 522 1713 176 577 543 1781 184 604 565 1854 6000 1829 179 587
3. 5 11 5 12 CRUISE PERFORMANCE 1 522 cna sek 5 13 LANDING PERFORMANCE unu cantine gun nci iia aa exa nsu ya aeu adis adem ui pna aaia 5 14 Page Date 19 February 2014 5 1 5 Pilot s Operating Handbook US Performance EXTRA 330LX Left blank intentionally 5 2 Page Date 19 February 2014 Pilot s Operating Handbook US 25 5 3 301 XTRA Performance SECTION 5 PERFORMANCE 5 1 GENERAL Performance data charts on the following pages are presented to facilitate the planning of flights in detail and with reasonable accuracy under various conditions The data in the charts have been computed from actual flight tests with the aircraft and engine in good condition and using average piloting techniques It should be noted that the performance information presented in the range and endurance charts allow for 45 minutes reserve fuel at specified speeds Some indeterminate variables such as engine and propeller air turbulence and others may account for variations as high as 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 5 1 1 Performance Charts Performance data are presented in tab
4. 915 7 NORMAL PROCEDURES annie Cx d ipta aee ioc ui aie 915 7 PERFORMANCE 915 7 19 2014 915 1 Section 915 Pilot s Operating Handbook US GARMIN GTX 330 Transponder EXTRA 330LX Left blank intentionally 915 2 Page Date 19 February 2014 Pilot s Operating Handbook US 2 Section 915 EXTRA 330LX GARMIN GTX 330 Transponder 915 1 GENERAL The Garmin GTX330 panel mounted Mode S Transponderis aradio transmitter and receiverthat fulfills the role of the airborne beacon equipment according to the requirements of the Air Traffic Radar Beacon System ATCRBS Its functionality includes replying to ATCRBS Mode A and C and Mode S interrogations The Mode S function will allow the ground station to individually select the aircraft by its Aircraft Address assigned to the aircraft by the aviation agency Itoperates onradar frequencies receiving ground radar interrogations at 1030 MHz andtransmitting acoded response of pulses to ground based radar frequency of 1090 MHz The GTX 330 15 equipped with IDENT capability that activates the Special Position Identification SPI pulse for 18 seconds Mode S transmit receive capability also requires 1090 MHz transmitting and1030 MHz receiving for Mode S functions In addition to displaying
5. M 920 5 920 6 Ue eC 920 7 920 7 DESCRIPTION OF THE SYSTEM cech irc arua 920 7 920 8 HANDLING SERVICING AND MAINTENANCE 242444222 12222 920 7 Page Date 19 February 2014 920 1 Section 920 Pilot s Operating Handbook US Airtow Hook XTRA EXTRA 330LX Left blank intentionally 920 2 Page Date 19 February 2014 Pilot s Operating Handbook US Section 920 EXTRA 330LX XTRA Airtow Hook 920 1 GENERAL The EXTRA 330LX can optionally be equipped with a TOST glider air tow release Typ E 85 The release mechanism is mounted at the tail spring end and actuated from the cockpit by a yellow knob 920 2 LIMITATIONS The following combinations are certified Aircraft Engine AEIO 580 B1A Propeller MTV 9 B C C 198 25 or MTV 14 B C C 190 130 Exhaust system Typ Gomolzig EA 300 606000 Air tow release system according to replacement instruction UA 300 4 95 Air tow release TOST E 85 Glider MTOW of the glider 765Kg 1687 105 Max air towing speed of the glider 152 km h or above Air tow cable and breaking piece weak links Length of the synthetic tow between 40 m 130 ft and 60 m 195 ft Ultimate load of the air tow max 850 kp 1875 Ibs If tows with higher ultimat
6. 8 3 8 5 SERVICING 8 4 8 6 cies bL Uuiulc 84 Page Date 19 February 2014 8 1 Section 8 Pilot s Operating Handbook US Handling Servicing and Maintenance EXTRA 330LX Left blank intentionally 8 2 Page Date 19 February 2014 Pilot s Operating Handbook US Section 8 EXTRA 330LX 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 Aservice 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 a
7. 2 15 Page Date 19 February 2014 2 1 Section 2 Pilot s Operating Handbook US Limitations XTRA EXTRA 330LX Left blank intentionally 2 2 Page Date 19 February 2014 Pilot s Operating Handbook US Section 2 X TRA Limitations EXTRA 330LX 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 on behalf of the FAA Observance of these operating limitations is required by national aviation regulations NOTE In case of an aircraft equipped with specific options additional information required for safe operation will be contained in Section 9 Supplements This aircraft is certified under FAA Type Certification Data Sheet N A67EU Any exceedance of given limitations has to be reported by the pilot so that necessary inspection or maintenance procedures according to the MAINTENANCE MANUAL EXTRA 330LX can be performed AIR SPEED IAS Never Exceed Speed Vue 219 406km h Max Structural Cruising Speed Acro Cat Il HI Vno 154 285km h Maneuver Speed Acro Cat Il 111 V 154 285km h Max Control Inputs Acro Cat Il HI upto 185knots 343km h CROSS WIND COMPONENT
8. 2 Wing Tie Down Rings 1 Canopy Lock 1 Heater 1 Battery 1 Battery Lightweight 1 Alternator 60 Amps 1 Alternator 65 Amps 1 Alternator 55 Amps 1 Shunt 100A 100mV 1 Volt Ammeter 1 External Power Socket Piper Type 1 Batt Charger Plug 12V 1 12VDC Power Outlet Socket 1 Safety Belt Assy Rear Seat seat belts w ratchet shoulder harness crotch strap 1 Safety Belt Assy Front Seat seat belts shoulder harness crotch strap 1 Safety Belt Assy Front Seat seat belts w ratchet shoulder harness crotch strap 1 First Aid Pack Flight Controls 27 1 Elevator Trim System Electric 1 Mechanically Adjustable Pedal Sys Venting and Heating 21 Extra Extra Extra Concorde Concorde Plane Power Prestolite Bosch Electronics International Electronics International Cole Hersee Extra Sutars Hooker Hooker Hooker Hartmann Ray Allen Extra EA 8D606 RG 25 XC RG 12LSA AL12 EI60 B 66021637 0 120 489 917 S 50 VA 1A 50 11041 06 EA 93102 18 1218 1011230 3 amp 1113012 1 1x 1H5630 3 2x 1CS924 D 1x 1011230 4x 1H3030 3 2x 1CS924 D 1x 1011230 3 amp 1113012 1 1x 1H3030 3 2x 1CS924 D 1x 7394280 EA 4D401 0 EA 46304 8C801 002 83401 001 LK Option 300 LT KBS01 03617 03617 33552 33558 33508 008 FA3007 PG 31731 0
9. Mode 914 6 Altitude 2 ree tr reae etra eeu Re eR ree cu da ea 914 6 Failure 914 6 BI pus 914 7 EMERGENCY PROCEDURES 3 5 desee depre 914 7 Imponan CODES escola 2 914 7 NORMAL PROCEDURES 1 tenen era d ipta aee ioc 914 7 PERFORMANCE 914 7 Page Date 19 February 2014 914 1 Section 914 Pilot s Operating Handbook US GARMIN GTX 328 Transponder EXTRA 330LX Left blank intentionally 914 2 Page Date 19 February 2014 Pilot s Operating Handbook US Section 914 EXTRA 330LX 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 and
10. 907 6 Page Date 19 February 2014 Pilot s Operating Handbook US Section 907 EXTRA 330LX X TRA Smoke System 907 8 HANDLING SERVICING AND MAINTENANCE At every refilling Check automatic shut off Additionally during the 100h Check 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 cables from smoke oil contamination NOTE The rudder cables might suffer from increased wear when they are covered with smoke oil and dust Page Date 19 February 2014 907 7 Section 907 Z Pilot s Operating Handbook US Smoke System XTRA EXTRA 330LX Left blank intentionally 907 8 Page Date 19 February 2014 Opening Handbook US XIRA SECTION 908 SINGLE SEAT CANOPY Table of Contents Paragraph Page 908 1 GENERAL 908 3 908 2 LIMITATIONS me 908 3 908 3 222204000448 cue e se nog 908 3 908 4 NORMAL PROCEDURES ga vean Ee ck ka coc Y AEREE 908 3 908 5
11. qud ua ndi n i aw aud ad i hu e 1 3 1 2 MANUFACTURER ra ri 1 3 1 3 c 1 3 1 3 1 3 VIOW DONIN ey cece Sane 1 3 1 3 2 1 4 1 3 3 WING o 1 4 1 3 4 Honzontal 1 4 1 3 5 Elevator 1 4 1 3 6 Vertical RNC 1 4 1 3 7 6 REX 1 4 1 4 duce 1 5 1 5 E 1 5 1 5 1 TID RR RI T E ULL LL 1 5 1 6 1 5 1 7 OIL eves cere 1 5 1 8 NePl ullcpmeee e 1 6 1 9 TERMINOLOGY lee 1 6 1 10 SECONDARY TERMINOLOGY ia in an nnn nda i caa n 1 7 1 11 GONVERSION TABLE iiaeiai acc unn paa une era oen ac n 1 7 Page Date 19 February 2014 1 1 Section 1 Pilot s Operating Handbook US General EXTRA 330LX Left blank intentionally 1 2 Page
12. RR 2 5 WEIGHT AND C G ENVELOPE ne 2 5 HOSGIVOO o Pes oH aser N 2 5 m 2 5 ACROBATIC MANEUVERS 2 6 2 6 FANG IM EM EET 2 6 LOAD FACTOR 2 7 2 7 2 7 FLIGHT GREW LIMITS 2 8 KINDS OF OPERATION LIMITS 2 8 Structural Temperature Colour 2 8 MAXIMUM OPERATING ALTITUDE 2 8 tnodo etes ecd tL 2 8 MARKINGS AND PLACARDS tanen a nunt nnn n assa sinn nsns a nnne nn nas 2 8 Aircratt Identification Plate i oe oce i bete taeda 2 8 Operating EL 2 9 Msrument 2 14 KINDS OF OPERATION EQUIPMENT LIST
13. 2220 26 913 6 israel e c 913 6 19 2014 913 1 Section 913 Pilot s Operating Handbook US GARMIN GTX 327Transponder EXTRA 330LX Left blank intentionally 913 2 Page Date 19 February 2014 Pilot s Operating Handbook US 2 Section 913 EXTRA 330LX GARMIN 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 TONG FLIGHT TIME 01 23 20 STOF The GTX 327 owner accepts all responsibility for obtaining the proper license before using the transponder The coverage you can expect from the GTX 327 is limited to line of sight Low altitude or aircraft antenna shielding by the aircraft itself may result in reduced range Range can be improved by climbing to a higher altitude It may be possible to minimize antenna shielding by locating the antenna where dead spots are only noticed during abnormal flight attitudes CAUTION The GTX 327 should be turned off before starting or shutting down aircraft engine
14. Pilot s Operating Handbook US Optional Primary Flight Display ASPEN Weight and Balance and Equipment List EXTRA 330LX QTY ITEM MANUFACT MODELNO PARTORP N WEIGHT ARM INST kg 1 Airspeed Ind front kts Mikrotechna Praha LUN 1106 K2B4 SC 34155 0 50 0 66 A reserved 1 Airspeed Indicator United Instr UI8030 B 882 32811 0 32 1 61 R rear kts 1 Airspeed Indicator United Instr UI8030 B 896 33630 0 32 1 61 A rear kts km h 1 Airspeed Ind rear kts Mikrotechna Praha LUN 1106 K2B4 SC 34155 0 50 1 61 A reserved 1 Alternate Static Valve Extra Assy 300 L Option 0 15 1 60 O StatLei 1 Altimeter front ft United Instr UI5934PD 3 30416 0 39 0 66 O A 134 reserved 1 Altimeter front ft Mikrotechna Praha LUN 1128 10B6 34159 0 59 0 65 A 1 Altimeter rear ft United Instr UI5934PD 3 30416 0 39 1 62 R A 134 reserved 1 Altimeter rear ft Mikrotechna Praha LUN 1128 10B6 34159 0 59 1 61 A reserved 1 Vertical Speed United Instr UI7030 C 27 01485 0 54 1 62 O Indicator fpm reserved 1 Vertical Speed Ind Mikrotechna Praha LUN 1144 B0B1 34161 0 40 1 61 A reserved 1 Attitude Gyro RC Allen RCA2600 2 0 tilt 33027 0 24 163 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
15. aod ce e aD Gc ck 908 3 908 6 WEIGHT AND BALANCE AND EQUIPMENT 115 222 11 1 908 3 908 7 DESCRIPTION OF THE SYSTEM nnne nennen tnmen nnns annt nnns 908 3 908 8 HANDLING SERVICE AND MAINTENANCE 908 3 Page Date 19 February 2014 908 1 Section 908 Z Pilot s Operating Handbook US Single Seat Canopy XTRA EXTRA 330LX Left blank intentionally 908 2 Page Date 19 February 2014 Pilot s Operating Handbook US Section 908 EXTRA 330LX 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 category ACRO 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 Th
16. EXTRA 330LX Left blank intentionally 3 2 Page Date 19 February 2014 Pilot s Operating Handbook US Section 3 EXTRA 330LX 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 performedin 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 the situation In any emergency situation contact should be established with a ground station as soon as possible after completing the initial corrective action Include position altitude heading speed nature of the emergency and pilot s intentions in the first transmission Thereafter 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
17. cold weather kit Starting 80 32865 30552 Ground Equipment 03543 31730 86100 000 24 3 74 4 26 0 85 R 0 85 Page Date 19 February 2014 Pilot s Operating Handbook US XTRA EXTRA 330LX Paragraph 7 1 7 2 7 3 7 4 7 5 7 5 1 7 5 2 7 5 8 7 5 4 7 5 5 7 6 7 6 1 7 6 2 7 7 7 8 7 9 7 10 7 10 1 7 10 2 7 10 3 7 10 4 7 10 5 7 10 6 7 10 7 7 10 8 7 10 9 7 11 7 12 7 13 SECTION 7 DESCPRIPTION amp OPERATION OF AIRCRAFT AND SYSTEMS Table of Contents Page THE 7 3 S N e E E E 7 3 lh M 7 4 sic 7 4 FLIGHT CONTROL SYSTEM 25 oiu iuret rennen nt kann oar nigdi 7 5 Primary Control System noce race 7 5 Longitudinal Flight Control System eee 7 5 Lateral Flight Control 7 b Directional Flight Control System ORE RR 7 5 Secondary ERE 7 5 INSTRUMENTATION 5 2 cotre nene cu rame e CO in er oio 7 5 Instrument Panel Rear
18. excess sacar M 907 5 907 6 WEIGHT AND 2 2 eere erasa coc NASAN Annan NERENN aa Rana EDD 907 5 907 7 DESCRIPTION OF THE SYSTEM 907 5 907 8 HANDLING SERVICING AND MAINTENANCE 907 7 Page Date 19 February 2014 907 1 Section 907 Z Pilot s Operating Handbook US Smoke System XTRA EXTRA 330LX Left blank intentionally 907 2 Page Date 19 February 2014 Pilot s Operating Handbook US Section 907 EXTRA 330LX X TRA Smoke System 907 SMOKE SYSTEM 907 1 GENERAL For performing at airshows the EXTRA 330LX 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 69 69 at 950kg 2 Specification of the smoke oil straight paraffin oil viscosity 30 50 cSt at 20 68 F initial boiling point gt 330 626 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 smok
19. CO SF SE LO SILO SILO S LO S LO SILO SJ LOIRE OINIOINISOINIOINI OINTOLR O CN tO IOI NTO RM QIN OILY O CN LO O CN LO O CN ewe Pes eed ed S GS SS 2SN SIQI NIS eG x NIN TA N 111 100 54 1500 152 z v E x x Z v E v N lt x lt x 9 c x Page Date 19 February 2014 Pilot s Operating Handbook US XIRA EXTRA 330LX 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 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 SECTION 2 LIMITATIONS Table of Contents Page ij zl 2 3 Ciel 2 3 CROSS WIND COMPONENT uec bacc cauaa ee Saa 2 3 ENGINE c M a 2 3 2 3 Engine LIMIA arrer NAS 2 4 2 552 2 5
20. 2 2L OF JL gt o ill g II I a 5 Lu 6 6 Page Date 19 February 2014 Pilot s Operating Handbook US 6 EXTRA 330LX Weight and Balance and Equipment List 6 3 1 Sample Take off Condition Pilot On Rear Seat 90 0 kg 198 5 Ibs Copilot On Front Seat 90 0 kg 198 5 Ibs 51 L Fuel in Acro Tanks 37 0 kg 81 5 105 101 L Fuel In Wing Tanks 73 0 kg 160 9 Ibs Aircraft Empty Weight 660 0 kg 1455 Ibs 950 0 kg 2094 4 Ibs To find C G follow line Pilot Rear Seat from Empty Weight to 90 kg 198 5 Ibs Point 1 Continue on line Copilot Front Seat to 90 kg Point 7 Now follow line Fuel via Point 8 51 L 13 5 US gal Acro Fuel to Point 9 101 L 26 6 US gal Fuel in Wing Tank FIND Weight 950 kg 2094 4 lbs C G 75 4 cm 29 6 inch 6 3 2 Weight and Balance Record Sheet WEIGHT MOMENT EMPTY WEIGHT PILOT COPILOT ACRO FUEL WING FUEL Xw xo 2 _ x Page Date 19 February 2014 6 7 Section 6 2 Pilot s Operating Handbook US Weight and Balance and Equipment List EXTRA 330LX 6 4 LOADING WEIGHTS AND MOMENTS OCCUPANTS max 2 WEIGHT PILOT COPILOT Pilot REAR SEAT FRONT SEAT Parachute Arm 207cm 81 5 inch Arm 98 cm 38 4 inch KGxCM INxLBS MOMENT KGxCM INxLBS 10758 5068 11654 5491 12551 5913 13447 6336 14344
21. 327 Transponder VFR Sets the transponder code to the pre programmed code selected in the Configuration Mode Pressing the VFR key again will restore the previous identification code START STOP Starts and stops the Count Up and Count Down timers CRSR Initiates entry of starting time for the Count Down timer and cancels transponder code entry 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 Controlled by the START STOP and CLR keys COUNT DOWN Controlled by START STOP CLR and CRSR keys The initial Count Down time is entered
22. 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 direct link http www extraaircraft com techserv asp where the Revision Index always shows the current revision status It the responsibility of the pilot to be familiar with the contents of this Flight Manual includ ing 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 FAA approval The editor has the copyright of this Flight Manual and is responsible 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 FAA 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 GmbH Flugplatz Dinslaken 46569 H nxe Federal Republic of Germany Should this Flight Manual be found kindly forward it to the civil b
23. 901 7 STEERABLE TAIL WHEEL GENERAL To improve taxi and handling quality the EXTRA 3301 X can be equipped with an optional steerable tailwheel The deflection angle of this tailwheel is arranged by the rudder control up to plus minus 30 Exceeding this deflection the tailwheel has a full swivel capability by a release mechanism LIMITATION The operation limitations are not effected due to the use of the steerable tailwheel EMERGENCY PROCEDURES There is no change of basic emergency procedures with the installation of the steerable tailwheel NORMAL PROCEDURES There are no changes for the described normal procedures after installation of the steerable tailwheel In addition to the existing normal procedures the light precompression of connec tor springs and movement of the rudder have to be checked during the preflight check PERFORMANCE Changes in flight performance due to installation of the steerable tailwheel are not notice able The given basic performance data under section 5 are still valid WEIGHT AND BALANCE A change of the running empty weight and resulting C G position after installation of the steerable tailwheel is neglectable because of minor differences in weight and C G between standard and optional steerable tailwheel DESCRIPTION OF THE SYSTEM The 5 inch tailwheel has a solid rubber tire and is rotatable by means of a wheelfork which is connected to a bearing steelsleeve This steelsleeve itself
24. Limitations 2 14 OPERATING PLACARDS 154 KTS ACRO near each 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 operating limitations which must be complied with when operating this airplane in this category are contained in the Airplane Flight Manual in the rear cockpit This airplane is certified for VFR day operation Operation under known icing conditions prohibited onthe rear instrument panel FUEL AVGAS 100 100LL near each filler cap on the seperate hatch of the upper cowling N R N M NA UP 0 A N 3 On the rear control stick On the rear instrument panel on the trim LED indicator Page Date 19 February 2014 2 9 Section 2 Pilot s Operating Handbook US Limitations EXTRA 330LX FUEL SELECTOR VALVE WING TANKS usable 120 L 31 7 US GAL CENTER ACRO 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 120L 31 7 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
25. Section 7 Description and Operation of Aircraft and Systems Pilot s Operating Handbook US EXTRA 330LX 518 519 NIYIN U9 IMS o p dX 1exeeug jexoos 161 2 C9 pueBe1 ASVLIOA C9 4 Ps 52 c funus 708 2 S HMd LX3 YOLVNYSLIV 2 d Figure 4 Electrical System 7 18 Page Date 19 February 2014 7 Pilot s Operating Handbook US Description and Operation of Aircraft and Systems X TRA EXTRA 330LX Left blank intentionally 7 14 Page Date 19 February 2014 Opening Handbook US XIRA SECTION 8 HANDLING SERVICING amp MAINTENANCE TABLEOF CONTENTS Paragraph Page 8 1 INTRODUCTION me A 8 3 8 2 AIRPLANE INSPECTION 8 8 3 8 3 PILOT CONDUCTED PREVENTIVE MAINTENANCE 4242412211 8 3 8 4 ALTERATIONS OR REPAIR 2
26. The Table of Contents shows all EXTRA Supplements available for the EXTRA 330LX A check mark in the Section column indicates that the corresponding supplement must be included in this POH Page Date 19 February 2014 9 3 Section 9 Z Pilot s Operating Handbook US Supplements XTRA EXTRA 330LX Left blank intentionally 9 4 Page Date 19 February 2014 Opening Handbook US XIRA SECTION 901 STEERABLE TAIL WHEEL Table of Contents Paragraph Page 901 1 GENERALE oes n 901 3 901 2 LIMITATION A E a 901 3 901 3 EMERGENCY 4 4222 901 3 901 4 NORMAL PROCEDURES 901 3 901 5 PERFORMANCE 901 3 901 6 WEIGHT AND BALANCE sconnessa aAa 901 3 901 7 DESCRIPTION OF THE SYSTEM anaa rar nnns 901 3 901 8 HANDLING SERVICING AND MAINTENANCE 901 4 Page Date 19 Februar 2014 901 1 901 Pilot s Operating Handbook US Steerable Tail Wheel XTRA EXTRA 330LX Left blank intentionally 901 2 Page Date 19 Februar 2014 Pilot s Operating Handbook US Section 901 EXTRA 330LX XTRA Steerable Tail Wheel 901 901 1 901 2 901 3 901 4 901 5 901 6
27. 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 19 February 2014 Pilot s Operating Handbook US Section 7 EXTRA 330LX 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
28. tte rtt rete re dete dts 3 4 Engine Failure immediately after 3 4 Engine Failure during Flight Restart 3 4 EE 3 5 IGM 3 5 Alternator FANUC es 2 rii 3 5 FORGED EY plc 3 6 Emergency Landing without Engine 2 ene 3 6 Precautionary Landing with Engine 3 6 3 6 During Start on Ground 3 6 Mee EET 3 7 Engine Fire im 3 7 IGING e 3 7 Inadvertent detur te eee 3 7 UNINTENTIONAL SPIN 2 12001 cnn Xon cauaa Ore 3 7 MANUAL BAILOUT 3 iri iacet et iunc cce uti cxi en esce gine nidis etes 3 7 EMERGENCY EXIT AFTER TURN OVER 3 8 ELEVATOR CONTROL FAILURE eeeeeeeeeeeeeee nennen nne nnnnn nnn nannten assit nnns sinn nnn n nn 3 8 Page Date 19 February 2014 3 1 Section 3 Pilot s Operating Handbook US Emergency Procedures
29. 0 56 INFORMATION MANUAL EXTRA 330LX MANUFACTURER EXTRA Flugzeugproduktions und Vertriebs GmbH Flugplatz Dinslaken 46569 H nxe Federal Republic of Germany WARNING This is an Information Manual and may be used for general purposes only This Information Manual is not kept current It must not be used as a substitute for the official FAA approved Airplane Flight Manual AFM Pilot s Operating Handbook POH required for operation of an U S registered airplane blank intentionally Pilot s Operatia Handbook US XIRA LOG OF REVISIONS Dates of issue for original and revised pages Date and sign of approval Original 19 2014 Approved by CSV Project N 0010009466 Date of Approval 07 March 2014 Page Date 19 February 2014 LOGOF EFFECTIVE PAGES Page Date Page Date 19 February 2014 Page Date 19 February 2014 Pilot s Operating Handbook US EXTRA 330LX Left blank intentionally Page Date 19 February 2014 dian iss 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
30. 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 100LL for alternate fuelgrades see latest revision of Lycoming S l No 1070 Total fuel capacity 189L 49 9US gal Usable fuel capacity 187L 49 4US 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 17 7US gal For acrobatic flight wing tanks must be empty Page Date 19 February 2014 2 3 Section 2 2 Pilot s Operating Handbook US Limitations EXTRA 330LX 2 4 2 ENGINE LIMITATIONS a Maximum Rotational Speed Take Off and Maximum Continuous 2600 rpm b Oil temperature Maximum 118 245 Maximum sump capacity 15 13L 16 US qt Minimum sump capacity 8 51L 9 US qt d pressure Minimum ldling 172 kPa 25 psig Normal 379 655 55 95 psig Starting Warm up Taxi and 793 kPa 115psig CAUTION It 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 fl
31. 6758 15240 7180 16137 7603 TOTAL FUEL CAPACITY 189 L 49 9 US gal ACRO amp CENTER TANK WING TANK kg kg x cm kg Ib Ib x in Ib 65 143 10 26 72 159 360 313 144 31 8 20 53 144 31 8 721 629 18 0 39 7 40 106 288 63 5 1442 1257 21 6 47 6 60 159 43 2 953 2164 1886 25 2 55 6 80 211 57 6 127 0 2885 2514 28 8 63 5 100 26 4 72 0 158 8 3607 3144 324 71 4 120 31 7 86 4 190 5 4328 3771 36 0 79 3 39 6 87 3 43 2 95 2 46 8 103 2 49 7 109 6 6 8 19 2014 Section 6 Pilot s Operating Handbook US Weight and Balance and Equipment List EXTRA 330LX 6 5 WEIGHTS AND MOMENTS LIMITS Weight kg Ibs 950 2095 900 1985 850 1918 820 1808 800 1764 750 1655 700 1544 650 1432 Cat Il Mox T O Cot ACRO I 62 66 70 74 78 82 86 Arm cm 24 4 25 9 27 5 29 1 30 7 32 2 33 8 inch Center of grovity cm inch Aft of the ref dotum EXAMPLE At 790 KG 1741 LBS and 640000 kgcm the C G location is 80 0 cm 31 4 aft of ref datum Page Date 19 February 2014 Section 6 Pilot s Operating Handbook US Weight and Balance and Equipment List EXTRA 330LX 6 6 EQUIPMENT LIST EXTRA 330LX S N QTY MANUFACT MODELNO PARTORP N WEIGHT ARM R INST
32. 98r1 in 921 986 9 01 826 616 082 6 8 Ove 010 1 3 89 Do OZ 5996 08r 62 152 vic d 81 qu 1010 1 389 De 0 0891 215 2271 Sev 0701 ZLE 268 2 2 010 1 Zv 1 6 962 068 esz 2 7 010 1 201 zie 698 592 922 969 61 GvS 991 oslus I0J0 L 3609 D001 AONVLSIC 33O 3PIV L 2151 1 6561 Sere 0008 9821 266 2511 ise 6281 0009 9601 vee 286 006 6421 000 866 982 752 019 0002 708 972 222 022 16 010 1 104 0 1 Vd 4021 89 8 vc 0008 201 Ele 6281 0009 9 8 92 6121 0007 8 822 019 0002 9 961 evo 8 16 010 1 09 Vd 9091 69 8 1 8672 0008 0921 066 09 6281 0009 6601 186 662 6121 0007 666 Sec 078 952 019 0002 108 vc 614 612 15 406 406 386 20 371 201 1 mE sqi 244 ose 1 Page Date 19 February 2014 920 6 Pilot s Operating Handbook US Z Section 920 EXTRA 330LX XTRA Airtow Hook CLIMBRATE Conditions Power 2500 Rpm and full throttle mixture rich Speed of the aircraft tow 80 KIAS 148 Km h Weight of the towing aircraft m 820 Kg 1808 Ib Tow force glider with m 350 kg 772 105 PA 0 32 F
33. ICS PILOT voL m 5 Annunciator 2 MODE Switch M MUSIC COPLT vo Dual Control Music Volume inner Copilot VOX outer LK LIVE SS MAX 910 4 Page Date 19 February 2014 Pilot s Operating Handbook US Section 910 EXTRA 330LX 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 setintercom volume Itis at minimum volume when fully counterclockwise ccw As the 15 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 controls 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 andif itis red itindicates VOX activity For transmit with sidet
34. Position down CLOSED Position left ACRO amp CENTER TANK Position up WINGTANK 7 10 9 EXHAUSTSYSTEM A complete Gomolzig 6 in 1 System with integrated silencer is installed on the 330LX 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 19 February 2014 Section 7 Description and Operation of Aircraft and Systems XTRA Pilot s Operating Handbook US EXTRA 330LX TIAHS NOILO3 LOHd d 439 NV 34 1 V34 SMNVL OOV ANY H31LN3O HLON LN3A Alddns 1303 a Q X 1304 ES 13nd 21412919 HOIV1OOSVO JAVA HOLO313S 1314 16 ANVL OHOV ff W EN sb 4 Ir 109 109 9NIM 2 YAONASNVYL ALO 1914 x 5INVI ONIM MOAN MOAN Yad ALO 7 11 Figure 3 Fuel System Page Date 19 February 2014 7 Neu Pilot s Operating Handbook US Description and Operation of Aircraft and Systems X
35. The GTX 327 Transponder is powered by pressing the 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 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 19 February 2014 913 3 Section 913 Pilot s Operating Handbook US GARMIN GTX 327Transponder EXTRA 330LX 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
36. 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 receiver whichever is currently selected by the tuning cursor Page Date 19 February 2014 916 5 Section 916 Z Pilot s Operating Handbook US GARMIN GNC 420W GNS 430W EXTRA 330LX 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 Thedirect to key provides access to the direct to function which allows you to enter a destination waypoint and establishes a direct course to the selected destination The MENU key displays a context sensitive list of options This options list allows you to access additional fea
37. 0000 to 7777 are possible Mode indication bottom line SBY mode 5 is displayed Mode A ON On appears in the display is displayed the duration of the identification function Mode A C ALT ff a valid altitude is present the flight level height in steps of 100 ft preceded by e g F241 24100 ft appears If no valid altitude code is present is diplayed The flight level display can be switched off in the configuration mode 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 ONTHEUNIT PRE FLIGHT CHECK 1 Checkthat the circuit breaker is set and switch on the aircraft power supply CAUTION Do not switch on the transponder if the motors or engines are being started or shut down 2 Usingmode switch A switch thetransponderfrom OFF to SBY Atestthenfollows automatically for 3 seconds The display is flashing with all digits and the unit is subject to a self test simultaneously Page Date 19 February 2014 Pilot s Operating Handbook US Section 911 XTRA BECKER 4401 Transponder EXTRA 330LX 3 Af
38. 330LX 906 8 PRESS AND RELEASE operation mode press and release in less than 2 3 of a second This operation mode is placarded below each button DIM R Masks L R During normal operation the tachometer presents the average of the left and right internal tachometers on the display However a mechanism exists to mask either tachometer from the display leaving the remaining tachometer to determine magneto ignition problems Quickly pressing and releasing the left button L causes the tachometer to mask the left tachometer Quickly pressing and releasing the right button R causes the tachometer to mask the right tachometer Dimmer DIM Quickly pressing and releasing the middle button DIM causes the tachometer to alternately dim or brighten the LED indicators except the large red LED of the rom Range HANDLING SERVICING AND MAINTENANCE Not affected 906 6 Page Date 19 February 2014 Opening Handbook US XIRA SECTION 907 SMOKE SYSTEM Table of Contents Paragraph Page 907 1 GENERAL EE 907 3 907 2 LIMITATIONS ee cane see 907 3 907 3 EMERGENCY 2 2242 44 4 4 0 012 907 3 907 4 NORMAL PROCEDURES 5 Intern In Ruine e XX FRE eon 907 4 907 5
39. 3424_EXT GENERAL TL 3424 EXT accelerometer can be installed as an option in the EXTRA 330LX Itis used in aspecial password protected configuration This configuration helps the pilot to operate the aircraft within limits In detail the 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 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 19 February 2014 904 3 Section 904 Pilot s Operating Handbook US Accelerometer TL 3424 EXT X TRA EXTRA 330LX 904 6 WEIGHT AND BALANCE Refer to the Equipment List in Section 6 of this Handbook 904 7 DESCRIPTION The complete installation consists of 5 O 010101010 1 TL 3424 EXTAccelerometer 2 G VLIMITS WARNING LIGHT 3 RS 232c
40. 493 913 Economy 2000 21 5 52 165 426 11 3 156 1 289 139 257 3 55 551 1020 Economy 2000 18 5 43 135 36 5 9 6 145 4 269 130 241 4 12 598 1107 Economy 8000 2600 21 7 73 231 73 4 19 4 179 6 333 162 300 2 08 367 680 Power 2438 2350 20 6 62 195 52 0 13 7 169 0 313 144 267 2 90 485 898 Economy 2050 20 6 52 165 43 0 11 4 159 3 295 137 254 3 49 552 1022 Economy 10000 2600 20 2 69 215 69 6 18 4 178 6 331 148 274 2 19 382 707 Power 3048 2500 192 62 195 53 6 142 1724 319 143 265 2 81 476 882 Economy 2150 19 3 52 165 437 11 5 162 5 301 136 252 3 42 549 1017 Economy 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 Q Leaning with exhaust gas temperature gage For the adjustment Best Power first lean the mixture to achieve the top exhaust temperature peak EGT and then enrich again until the exhaust temperature is 100 F lower than peak EGT For the adjustment Best Economy simply lean the mixture to achieve the top exhaust temperature peak EGT CAUTION Always return the mixture to full rich before increasing power settings Page Date 19 February 2014 5 13 Section 5 Performance Pilot s Operating Handbook US EXTRA 330LX
41. 5 T9 12 a T a 10 9 i 7 5 5 T 4 3 e 1 60 40 20 0 20 40 60 TEMPERATURE Page Date 19 February 2014 5 5 5 Pilot s Operating Handbook US Performance EXTRA 330LX 5 3 AIRSPEED CALIBRATION CAS km h 90 110 130 150 170 190 210 230 250 270 290 310 330 350 370 390 410 o 5 ER ENGEL LEE HH 03 22 2 AAN EEEE EE IAS km h 50 60 70 80 90 100 110 120 130 140 150 160 170 180 190 200 210 220 KCAS NOTE Indicated airspeed assumes zero instrument error 5 6 Page Date 19 February 2014 Pilot s Operating Handbook US EXTRA 330LX X TRA TE a 5 4 STALLSPEED CONDITION POWERIDLE FORWARD C G STALL SPEEDS ANGLE OF BANK WEIGHT CATEGORY 0 30 45 60 10 1 150 1 419 20 105 KIAS km h KIAS km h KIAS km h KIAS km h 950 ACROIII 64 69 76 91 2095 119 128 141 169 870 61 66 73 87 1918 113 122 135 161 820 ACROI 59 64 71 84 1808 109 119 131 156 Max altitude loss during stall recovery is approximately 100 ft 30 m Page Date 19 February 2014 Section 5 Performance Pilot s Operating Handbook US EXTRA 330LX XTRA 5 5 TAKE OFF PERFORMANCE Power T O Power Runway Concrete NOTE For every 5 kts 9 k
42. 5 12 m 16 80 ft 1 80 m 5 91 ft 8 0 m 26 25 ft 10 72 m 115 39 2 155 125 1 85 m 6 07 ft 0 83 m 2 72 ft 1 405 m 4 61 ft 2 x 0 839 m 2 x 9 03 ft 2 x 0 876 m 2 x 9 43 ft up down 309 tolerance 2 3 20 m 10 50 ft 2 56 m 27 56 ft Wortmann FX71 L 150 30 0 768 m 8 27 ft up 25 toler 2 down 25 toler 2 up 35 down 27 tolerance 2 1 55 m 16 68 ft Wortmann FX 71 L 150 30 0 68 m 7 32 ft 0 75 m 8 07 ft left right 30 tolerance 2 Page Date 19 February 2014 Pilot s Operating Handbook US Section 1 EXTRA 330LX XTRA General 1 4 ENGINE Manufacturer Textron Lycoming Williamsport Plant PA 17701 USA Type Lycoming AEIO 580 B1A Rated power 315 HP 235 kW 2700 RPM 303 HP 226 kW 2600 RPM 286 HP 213 kW 2400 RPM 1 5 PROPELLER Manufacturer MT Propeller Entwicklung GmbH Federal Republic of Germany Type MTV 9 B C C 198 25 3 blade constant speed Alternative MTV 14 B C C190 130 4 blade constant speed 1 5 1 EXHAUSTSYSTEM Manufacturer Gomolzig Flugzeug und Maschinenbau GimbH Federal Republic of Germany Complete 6 in 1 System with integrated Silencer 1 6 FUEL Fuel type AVGAS 100 100 LL for alternate fuel grades see later issues of Textron Lycoming 5 1 No 1070 Minimum 100 130 octane Maximum 1 15 145 octane Total fuel capacity 189L 49 9US gal Wingtanks 2 x 60 L 120L 31 7US gal Center tank 60L 1
43. 553 1814 186 610 575 1886 194 636 598 1962 5 14 Page Date 19 February 2014 Pilot s Operating Handbook US XIRA EXTRA 330LX Paragraph 6 1 6 2 6 2 1 6 3 6 3 1 6 3 2 6 4 6 5 6 6 SECTION6 WEIGHT AND BALANCE AND EQUIPMENT LIST Table of Contents Page GENERAL 6 3 AIRCRAFT WEIGHING PROCEDURE 6 3 Owners Weight and Balance 4 6 4 CENTER OF GRAVITY CALCULATION SAMPLE PROBLEM 6 5 Srje m EIS 6 7 Weight and Balance Record Sheet 6 7 LOADING WEIGHTS AND annen nnn 6 8 WEIGHTS AND MOMENTS LIMITS eeeeeeeeeeeeeseeeeeneen nennen nenne nennen 6 9 EQUIPMENT LIST 6 10 Page Date 19 February 2014 6 1 Section 6 Pilot s Operating Handbook US Weight and Balance and Equipment List EXTRA 330LX Left blank intentionally 6 2 Page Date 19 February 2014 Pilot s Operating Handbook US Section 6 EXTRA 330LX 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 t
44. 9 2 Page Date 19 February 2014 Pilot s Operating Handbook US Section 9 EXTRA 330LX Supplements 9 SUPPLEMENTS 9 1 Introduction Section 9 Supplements of the Pilot s Operating Handbook contains all information neces sary for a safe and efficient operation of the airplane when equipped with one or more of the various optional systems and equipment not provided with the standard airplane 9 2 Notes The described systems and equipment are certified by the EASA on behalf of the FAA for the EXTRA 330LX 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 FAA 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 ofthis Pilot s Operating Handbook Each Supplement section e g steerable tailwheel covers only a single system device or piece of equipment is a self contained miniature Pilot s Operating Handbook The owner is responsible for incorporating prescribed amendments and should make notes about these on the records of amendments It is responsibility of the pilot to be familiar with the contents of relevant supplements POH Supplements must be in the airplane for flight operations when the subject equipment is installed or special operations are to be performed
45. Above apply for positive and negative spinning To stop the spin Apply opposite rudder Make sure power idle Holdailerons neutral Stick to neutral position The plane will recover within 1 2 turn Recovery can still be improved by feeding in in spin ailerons NOTE If ever disorientation should occur during spins normal or inverted one method always works to stop the spin Power idle Kick rudder to the heavier side this will always be against spin direction Take hands off the stick The spin will end after 1 2 turn The plane will be in a steep dive in a side slip Recovery to normal flight can be performed easily NOTE After six turns of spinning the altitude loss including recovery is 3200 ft 4 13 NOISE CHARACTERISTICS The noise level with silencer Gomolzig EA300 606000 6 in 1 and propeller MTV 9 B C C 198 25 at 2600 RPM has been established in accordance with FAR 36 Appendix G Amendment 28 as 77 5 dB A The noise level with silencer Gomolzig EA300 606000 1 and propeller MTV 14 B C C 190 130 at 2600 RPM has been established in accordance with FAR 36 Appendix Amendment 28 as 74 2 dB A 4 12 Page Date 19 February 2014 Pilot s Operating Handbook US Section 4 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
46. Aircraft and Systems X TRA EXTRA 330LX 7 10 3 ENGINEINSTALLATION The engine is supported by four shock mounts type BARRY CONTROLS to the tig welded steel tube engine mount which is attached to the fuselage with four bolts on the firewall axis The engine cowling is divided into two parts a lower and an upper part both made of glass fibre carbonfibre reinforced epoxy The parts are fixed by a number of screws and the upper cowling has a separate hatch for easy access to the oil dip stick 7 10 4 PROPELLER The standard propeller is a 3 blade wood composite constant speed MT V 9 B C C 198 25 type propeller having a diameter of 1 98 m 77 95 in Alternatively a 4 blade constant speed MT V 14 B C C 190 130 propeller can be installed This propeller has a diameter of 1 90 m 74 8 in 7 10 5 THROTTLE Dual control cub type mounted on the left side of the cockpit 7 10 6 MIXTURE Vernier control located at the left side of the rear cockpit red knob 7 10 7 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 Tank fuel supply
47. Around Speed 93 172 98 181 102 189 Recommended Airspeed For Flight In Rough Air max Va 154 285 154 285 154 285 Max Demonstrated Cross Wind Component 15 27 15kts 27 15kts 27 4 0 2 CHECKLIST AND PROCEDURES This handbook contains the checklist and procedures to operate the aircraft The pilot should be familiar with all procedures contained in this Pilot s Operating Handbook which must be carried on board The pilot has to comply with the checklist for daily checks and inspections see Section 8 Handling Servicing and Maintenance Page Date 19 February 2014 4 3 Section 4 Pilot s Operating Handbook US Normal Procedures EXTRA 330LX 4 1 PREFLIGHTINSPECTION 4 1 1 EXTERIORINSPECTIONILLUSTRATION 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 amp CENTER TANK position 2 Empennage 1 All round inspection canopy surfaces stabi
48. C indicates FN AI DEF inverted 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 19 February 2014 Pilot s Operating Handbook US Section 912 EXTRA 330LX 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 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 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 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 back to mode indication If STO b
49. CALLSIGN In both cockpits For N 030 060 120 150 sc For S 210 240 W 300 330 Za Near Mag Dir Indicator Page Date 19 February 2014 2 11 Section 2 Pilot s Operating Handbook US Limitations EXTRA 330LX 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 11111 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 In both cockpits on the RH side 2 12 Page Date 19 February 2014 Pilot s Operating Handbook US Section 2 EXTRA 330LX Limitations Approved acrobatic maneuvers and recommended entry airspeeds Maneuvers Airspeeds Maneuvers Airspeeds minKIAS maxKIAS min KIAS maxKIAS Segment Horizontal Line Aileron roll 45 climbing Snap roll 90 up Tail slide 45 diving Spin 90 diving Inverted spin 1 4 Loop climb Inverted flight Less than 4 min Loop Knife edge Stall turn
50. Date 19 February 2014 Pilot s Operating Handbook US Section 1 EXTRA 330LX XTRA General 1 0 1 1 1 2 1 3 1 3 1 DESCRIPTION The fuselage of the EXTRA 330LX is built of a tig welded steel tube construction Wings empennage and landing gear are manufactured from composite material Theaircraftis a two seater with the rear cockpit equipped with a complete set of airplane controls and instruments SPECIFICATION OF CLASS The aircraft is certified in the acrobatic category MANUFACTURER EXTRA Flugzeugproduktions und Vertriebs GmbH Flugplatz Dinslaken 46569 H nxe Federal Republic of Germany TECHNICALDATA 3 VIEW DRAWING Page Date 19 February 2014 1 3 General Pilot s Operating Handbook US EXTRA 330LX 1 3 2 MAINDATA Length Height Span Wheel base Wheel track 1 3 3 WING Wing span Wing area Airfoil Root Airfoil Tip Chord Root Chord Tip MAC area without horn balance Aileron area with horn balance 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 without horn balance Area with horn balance Rudder deflection 7 20 m 23 06 ft 2 62 m 8 60 ft 8 00 m 26 25 ft
51. Indicated air speed Indicated speed in knots True air speed It s the same as CAS compensated for altitude temperature and density Maneuvering speed Never exceed speed Maximum structural crusing speed Stalling speed or minimum steady flight speed Best angle of climb speed Bestrate of climb speed Page Date 19 February 2014 Pilot s Operating Handbook US Section 1 EXTRA 330LX XTRA General Meteorological terminology ISA International standard atmospheric condition OAT Outside air temperature 1 10 SECONDARY TERMINOLOGY fom Feet minute ft Feet 0 3048 m in inch 2 54 cm m Meter L Litres US gal US liquid gallon 3 79 litres US qt US liquid quart 0 946 litres hp Horse power english h Hour kts Knots nm h 1 852 kilometer per hour km h Kilometer per hour lbs English pound 0 4536 kg hPa hekto Pascal inHg Inches of mercury MP Manifold pressure PA Pressure altitude ft nm Nautical miles 1 852 km rom Revolutions per minute CG Center of gravity Arm Arm is the horizontal distance from reference datum Moment is the product of weight of an item multiplied by its arm Page Date 19 February 2014 1 7 EXTRA 330LX Pilot s Operating Handbook US XTRA CONVERSION TABLE Section 1 General 1 11 LO OINININ 00 CO O tO O CO DOJO O C Om LO CN Ob C cO OO sr 0
52. 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 19 February 2014 909 7 Section 909 Pilots Operating Handbook US ARTEXME 406 ELT EXTRA 330LX Left blank intentionally 909 8 Page Date 19 February 2014 Pilot s Operating Handbook US XTRA EXTRA 330LX Paragraph 910 1 910 1 1 910 2 910 3 910 4 910 5 910 6 910 7 910 7 1 910 7 2 910 7 3 SECTION 910 NAT AA83 001 INTERCOM Table of Contents Page g 910 3 AG USUIMSMMNS LEM 910 3 LIMITATIONS e M 910 3 EMERGENCY PROCEDURES in nannan OSEE 910 4 NORMAL PROCEDURES rennen eec eo vn 910 4 PERFORMANCE PEES 910 4 WEIGHT AND BALANCE eec ce ccr enun cr nnne pn cor Ranma 910 4 SYSTEM DESCRIPTION 2 2 6c Y argu spa cr Pru recep Ec 910 4 Controls and Indicalors er re IR Tex eR EUR o Fee nag Unna dedaduvavhadeceanavivaaacadebennivanad 910 4 Seri 910 6 Adalto la o
53. Less than 10s in both cockpits Page Date 19 February 2014 2 13 Section 2 Pilot s Operating Handbook US Limitations EXTRA 330LX 2 14 53 INSTRUMENT MARKINGS AIRSPEED INDICATOR greenarc 64 5 119 km h 154 KIAS 285 km h yellow arc 154 KIAS 285 km h 219 KIAS 406 km h redline 219 KIAS 406 km h OILPRESSURE 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 OIL TEMPERATURE INDICATOR yellow arc lt 140 F greenarc 140F 210 yellow arc 210 245 redline 245 CYLINDERHEAD TEMPERATURE INDICATOR yellow arc lt 150 F greenarc 150 F 435 yellow arc 435 F 465 F redline 465 RPMINDICATOR greenarc 700 rpm 2600 rpm red line 2600 rpm G METER green arc 5g 89 yellow arc 8g 109 redline 10g FUEL FLOW INDICATOR greenarc 0 gal h 35 gal h red radial 35 gal h MANIFOLD PRESSURE INDICATOR greenrange 10 Hg 30 Hg 2 14 Page Date 19 February 2014 Pilot s Operating Handbook US Section 2 EXTRA 330LX XTRA Limitations 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
54. OAT 10 i 1000 305 2000 610 3000 914 4000 1219 5000 1524 6000 1829 7000 2134 8000 2438 Tow force glider with 600 kg 1323 Ibs PA 0 32 F OAT 10 50 F 20 C e 1 1000 305 2000 610 3000 914 4000 1219 5000 1524 6000 1829 7000 2134 8000 2438 0 C 32 F 10 C 50 F 20 C 68 F 30 C 86 F SL 1000 305 2000 610 3000 914 4000 1219 5000 1524 6000 1829 7000 2134 8000 2438 Page Date 19 February 2014 920 7 Section 920 Z Pilot s Operating Handbook US Airtow Hook EXTRA 330LX 920 0 WEIGHT AND BALANCE Not affected 920 7 DESCRIPTION OF THE SYSTEM The release mechanism is a typ E 85 of the TOST company Munich It is mounted at the tail spring rear end aft the tail wheel and activated with a yellow handle located at the rear seat cockpit via a bowden cable 920 8 HANDLING SERVICING AND MAINTENANCE Service and maintenance needs to be conducted in accordance with the latest operation handbook Typ E 85 of the manufacturer TOST GmbH Germany Additionally during the 100 h inspection the bowden cable and the release handle have to be checked 920 8 Page Date 19 February 2014 Pilot s Operating Handbook US XTRA EXTRA 330LX 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
55. 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 Not affected 9076 WEIGHT AND BALANCE sf e s Weight of the paraffin oil 0 85 NOTE The smoke system does not feature a capacity dipstick In the case of unknown filling the smoke oil tanks should be drained and refilled with a known quantity If this is not possible the most adverse case has to be taken for CG calculation This may be either completely full or completely empty tanks 907 7 DESCRIPTION OF THE SYSTEM On pilot s demand the smoke system produces a trail of smoke by injection of smoke oil straight paraffin oil into the engine exhaust The smoke oil is vaporised by the exhaust gas heat and is visible as dense smoke after leaving the exhaust For smoke system activation the SMOKE ARM switch located on the pilot instrument panel needs to be switched ON first The smoke ON OFF toggle switch is located on top of the Page Date 19 February 2014 907 5 Section 907 Pilot s Operating Handbook US Smoke System XTRA EXTRA 330LX 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
56. Owners Weight and Balance Record Enter below all weight change data from aircraft log book EXTRA330LX SERIALNUMBER Date Description of Weight change Running empty modification Added Removed weight Wt kg Arm cm Moment kg cm Wt kg Moment kg cm lbs inch lbs inch lbs Ibs inch Empty weight asdelivered Page Date 19 February 2014 Pilot s Operating Handbook US Section 6 EXTRA 330LX Weight and Balance and Equipment List 6 3 CENTER OF GRAVITY CALCULATION SAMPLE PROBLEM PILOT ACRO TANK COPILOT WING TANK Rear Seat Fuel Front Seat Fuel Position 51LTR 120LTR 13 4 US GAL 31 7 US GAL kg lbs kg lbs PILOT ACRO TANK COPILOT WING TANK Rear Seat Fuel Front Seat Fuel Position 51LTR 101LTR 13 4 US GAL 26 7 US GAL kg Ibs Page Date 19 February 2014 6 5 Section 6 Pilot s Operating Handbook US Weight and Balance and Equipment List EXTRA 330LX E 99 Avda MUNACNNAUNCNAUNN SUSAN UN x 7 6 6 3 CENTER OF GRAVITY CALCULATION SAMPLE PROBLEM lt zs 7j E _ E 2 4 1 A i i X E zd Y n LJ LJ Wi 1 O 2
57. Pilot s Operating Handbook US EXTRA 330LX RANGE 5 8 00 000 wy 00 000 WN 007 006 WN 99 lt 49 04 909 Jie episino 55914 1 0008 98 aduwea 006 008 007 009 005 007 006 000 00 0 2 o gt e c 9 1 apis no Ov 06 Oc OL 0 01 00 06 OF 5 11 Page Date 19 February 2014 EXTRA 330LX Pilot s Operating Handbook US XTRA ENDURANCE Section 5 Performance 5 9 souesnpug 9 1 aunjesadwia 0 008 056527 002 Ov 06 OZ OL 0 01 02 O OF U 06 lt JeMog 09 enjejeduiej Sseug y 0008 esini ejduex3 y Ajsueq amod je Gp jo eeseJ e 10 6 SN 19 1 e xe pue dn 10j SA 6 1 6 sse jeb SN 6 1 ZBL 18n 810 91 v60z 056 1 Page Date 19 February 2014 512 Pilot s Operating Handbook US Section 5 EXTRA 330LX Performance 5 10 CRUISE PERFORMANCE Configuration T O Weight 950 kg 2095 Ib Acro amp Center Tank Fuel Capacity Total Fuel Capacity 69 L 18 2 US gal 189L 49 9 US gal Range and Endurance values include fuel for warm up and Take Off from SL max cont
58. Power climb to cruising altitude and a reserve of 21 L 5 55 US gal for 45 minutes with 45 Power 2 L 0 53 US gal unusable fuel is taken into account At ISA Conditions PA Eng Manif PowerSetting Fuel TAS IAS Endur Range Mixture Press Consumption ft m rpm inHg hp kts km h kts km h h km Best 2000 2600 27 2 91 286 88 2 23 3 182 6 338 169 313 1 73 317 587 Power 610 2400 24 0 71 225 687 18 2 167 6 310 156 289 2 22 373 691 Power 2200 232 62 195 50 5 13 3 159 3 295 149 276 3 03 481 891 Economy 2000 22 5 52 165 42 6 11 3 150 2 278 141 261 3 59 538 996 Economy 2000 19 4 43 135 36 5 9 6 139 9 259 132 244 4 18 584 1082 Economy 4000 2600 252 85 267 827 21 9 181 5 336 164 304 1 85 333 617 Power 1219 2400 23 4 71 225 687 18 2 170 9 317 154 285 2 22 378 700 Power 2200 22 7 62 195 50 5 13 3 162 4 301 147 272 3 02 487 902 Economy 2000 21 8 52 165 42 6 11 3 153 1 284 140 259 3 57 544 1007 Economy 2000 19 0 43 135 36 5 9 6 142 6 264 131 243 4 18 591 1095 Economy 6000 2600 23 4 79 248 77 6 20 5 180 5 334 158 293 1 97 351 650 Power 1829 2500 222 71 225 698 18 4 174 3 323 153 283 2 19 377 698 Power 2200 222 62 195 50 5 13 3 165 6 307 146 270 3 00
59. TRA EXTRA 330LX Wing Tank The root section of each wing in front of main spars forms an integral fuel tank providing two interconnected tanks with 120 liters 31 7 US GAL total capacity Each side of the wing has a 2 diameter filler cap for gravity refueling The wing tank can be completely emptied in flight Acro amp Center Tank An Acro tank 9 liters 2 3 US Gal is mounted in the fuselage just behind the firewall and the Center tank 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 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 ELECTRICALSYSTEM The electrical system refer to Figure 4 is supplied by a 12 V alternator
60. 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 onthe 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 ofthe 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 19 February 2014 922 5 Section 922 Z Pilot s Operating Handbook US GARMIN GTN 635 650 750 XTRA EXTRA 330LX 922 26 GLOVEUSE No device may be used 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
61. The aircraft EXTRA 330LX 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 in the acrobatic category to fullfill the primary flight training normal operation rules and acrobatic training up to the unlimited acrobatic level EXTRA 330LX is a light weight robust single piston engined two seat aircraft with a fuselage structure in tig welded steel tube construction The landing gear wing and tail are made of epoxy reinforced with glass and carbonfiber The items are qualified up to 72 C 161 69 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 72 161 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 with the preflight checklist Below 72 C 161 6 b At 72 C 161 6 F or above STRUCTURAL CAUTION STRUCTURAL CAUTION OVERHEAT emu ee OVERHEAT While
62. 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 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 19 February 2014 Pilot s Operating Handbook US Section 915 EXTRA 330LX GARMIN GTX 330 Transponder 915 2 LIMITATIONS Notapplicable 915 3 EMERGENCY PROCEDURES 915 3 1 IMPORTANT CODES 7600 Loss of communications 7500 Hijacking 7700 Emergency All secondary surveillance radar sites are ready to receive this code at all times See the Airman s Information Manual AIM for a detailed explanation of identification codes 915 4 NORMAL PROCEDURES Not applicable 915 5 PERFORMANCE Not applicable Page Date 19 February 2014 915 7 Section 915 Pilot s Operating Handbook US GARMIN GTX 330 Transponder EXTRA 330LX Left blank intentiona
63. 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 that provides a visual display of both controls and functions The required controls are displayed for the 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 Map displays 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 Volume knob controls audio volume for the selected COM radio or NAV receiver if installed and any external audio input devices if installed When the COM radio is active press the Volume kno
64. 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 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 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 259909999090 SMOKE SMOKE LANDING ARM REFILL LIGHT C 15 10 9 9 9 SMOKE LANDING SYSTEM LIGHT 9 9 9 t
65. at into or out of any airport The above noise levels were established at 950 kg 1980 Ibs takeoff weight This aircraft model is in compliance with FAR 36 noise standards applicable to this type Page Date 19 February 2014 4 13 4 Pilot s Operating Handbook US Normal Procedures EXTRA 330LX Left blank intentionally 4 14 Page Date 19 February 2014 Pilot s Operating Handbook US XIRA EXTRA 330LX 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 SECTION5 PERFORMANCE Table of Contents Page GENERAL e 5 3 Performance 5 3 Definitions Of Em 5 3 Sample 5 3 ISA CONVERSION 5 5 AIRSPEED CALIBRATION pa acp adn 5 6 STALE SPEED 5 7 TAKE OFF PERFORMANCE 2 0 20 5 8 RATE OF CLIMB mu aan 5 9 TIME TO CLIMB FUELTO CLIMB aaiae iaeia Saaai eiia 5 10 E
66. below 1 Flash Indicates that the system is operational and that no error conditions were found 3Flashes Bad load detected Detects open or short condition on the antenna output or cable These problems can probably be fixed by the installer Check that the RF cable is connected and in good condition Perform continuity check of center conductor and shield Check for a shorted cable Check for intermittent connection in the RF cable 909 6 Page Date 19 February 2014 Pilot s Operating Handbook US Section 909 EXTRA 330LX XTRA ARTEX ME 406 ELT e If this error code persists there may a problem with the antenna installation This can be checked with a VSWR meter Check the antenna for opens shorts resistive ground plane connection 4Flashes 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 5Flashes Indicates that ELT has not been programmed or is incorrectly programmed Does notindicate erroneous or corrupted programmed data 6Flashes Indicates that the G switch loop between pins 5 and 12 at the D sub connector is not installed ELT will not activate during a crash e Check that the harness D sub jumper is installed by verifying less than 1 ohm of resistance between pins 5 and 12 7
67. contains also the release mechanic which gives the wheelfork a full swivel capability exceeding plus minus 30 deflection The steelsleeve is glued into the glasfiberspring which is bolted to the tail hardpoint of the aircraft The steering of the tailwheel is accomplished by a direct mechanic link rudder control cable from the rudder pedals The steering deflection of the tailwheel is controlled by the rudder movement and dampened by anti shimmy connector springs Page Date 19 Februar 2014 901 3 901 Pilot s Operating Handbook US Steerable Tail Wheel XTRA EXTRA 330LX 901 8 HANDLING SERVICING AND MAINTENANCE During 50 hour inspection the bearing steel sleeve has to be lubricated on the point of lubri cating Additionally all parts of the tailwheel have to be inspected visually for deformations cracks and corrosion 901 4 Page Date 19 Februar 2014 Operating Handbook US XIRA SECTION 902 ELECTRIC PEDAL ADJUSTMENT Table of Contents Paragraph Page 902 1 GENERAL 9 902 3 902 2 LIMITATIONS me 902 3 902 3 EMERGENCY PROCEDURES 902 3 902 4 NORMAL PROCEDURES 902 3 902 5 dde i esc PP 902 3 902 6 WEIGHT AND BALANDGE onore corn deci
68. e 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 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 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 19 February 2014 7 3 7 Neu Pilot s Operating Handbook US Description and Operation of Aircraft and Systems X TRA EXTRA 330LX 7 3 WING The wing is a CRP construction The dual chamber main spar b
69. keys After power on a start up page will be displayed while the unit performs a self test Thissupplementis written for software version 5 00 or later andis not suitable for earlier software versions Some differences in operation may be observed when comparing the information in this supplementto later software versions Verify the information herein with the GTX 328 pilot s guide PN 190 00420 03 applicable revision you received with your transponder There you find also further information Page Date 19 February 2014 914 3 Section 914 Pilot s Operating Handbook US GARMIN GTX 328 Transponder EXTRA 330LX 914 1 1 MODESELECTIONKEYS 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
70. 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 music 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 19 February 2014 910 7 Section 910 Ki Pilot s Operating Handbook US NAT AA83 001 Intercom EXTRA 330LX The relative volume ofthe music can be changed from the panel by the knob marked with a musical note Below is simple chart to aid in understanding audio switching in the NORMAL Operation mode function The following terms are used Active Function being used Muted Functions that are ov
71. 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 922 4 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 922 5 PERFORMANCE Not affected Page Date 19 February 2014 922 7 Section 922 Z Pilot s Operating Handbook US GARMIN GTN 635 650 750 XTRA EXTRA 330LX 922 6 WEIGHT amp CENTER OF GRAVITY Refer to the equipment list in Section 6 of this Handbook 9227 SYSTEMDESCRIPTION 922 7 1 TOUCHSCREEN KEY AND KNOB FUNCTIONS Controls
72. 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 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 19 February 2014 Pilot s Operating Handbook US Section 4 EXTRA 330LX XTRA Normal Procedures Segment 90 up Any entry speed may be used Out of a horizontal pull up at 200 KIAS 370 km h the vertical penetration will be 2 500 ft The speed will gradually decrease to 0 NOTE In extremely long lines a RPM decay may occur This is related to a loss of oil pressure Positive g s should be pulled immediately in order to protect the engine 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 be filled up with aileron rolls or snap rolls Watch V 154 KIAS 285 km h for aileron rolls with max deflection Snap rolls should not be performed at
73. 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 previous digit Pressing the CLR Key when the cursor is on the first digit of the code or pressing the CRSR Key during code entry removes the cursor and cancels data entry restoring the previous code Press the CLR Key up to five seconds after code entry is complete to return the cursor to the fourth digit The numbers 8 and 9 are not used for code entry only for entering a Count Down time and contrast and display brightness IMPORTANT CODES 1200 The VFR code for any altitude in the US Refer to ICAO standards elsewhere 7000 The VFR code commonly used in Europe Refer to ICAO standards 7500 Hijack code Aircraft is subject to unlawful interference 7600 Loss of communications 7700 Emergency 7777 Military interceptor operations Never squawk this code 0000 Military use Not enterable 914 4 Page Date 19 February 2014 Pilot s Operating Handbook US Section 914 EXTRA 330LX GARMIN 328 Transponder Avoid selecting codes 0000 7500 and
74. 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 transmitter Due to the 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 outside on the left fuselage in the vicinity of the ELT unit next to the ELT remote switch gt z v 3 gt 2 FOR AVIATION EMERGENCY USE ONLY UNAUTHORIZED OPERATION PROHIBITED aS close to the ELT remote switch as practical Page Date 19 February 2014 909 3 Section 909 Z Pilots Operating Handbook US ARTEX ME 406 ELT EXTRA 330LX 9093 EMERGENCY PROCEDURES Incase 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
75. 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 AK WARNING Make only one attempt to restore an automatically disconnected power source 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 automatically disconnected CPD can result in progressively worse effects Page Date 19 February 2014 3 3 Section 3 Pilot s Operating Handbook US Emergency Procedures EXTRA 330LX 3 1 AIRSPEEDS FOR EMERGENCY OPERATION Stall speed 64 KIAS 119 km h Engine failure after take off 90 KIAS 167 km h Best recommended gliding speed glide angle 1 6 2 Acro Ill Category 950 kg 2095 Ibs 90 KIAS 167 km h Acro Il Category 870 kg 1918 lbs 87 KIAS 161 km h Acro Category 820 kg 1808 lbs 85 KIAS 157 km h Precautionary landing with en
76. 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 Notapplicable 911 8 Page Date 19 February 2014 Pilot s Operating Handbook US XTRA BECKERB EXTRA 330LX 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 GENERAL M 912 3 Controls 912 4 Switching on the Unit pre flight check 912 4 Bier HH 912 5 fet eere 912 5 SQUAW T 912 6 Selftests of the Unit 8 912 6 Selection Mode cito e ese 912 7 Flight Operation in Mode A C S reply code and altitude code 912 9 VER COJE I T 912 10 Configuration Mode 912 10 BI gpule 912 10 EMERGENCY PROCEDURES 912 10 Impo
77. 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 ACROBATIC 1 seat 2 seats COMMUNICATION 1 Transceiver VHF 1 1 ELECTRICAL POWER 1 Battery 1 1 2 Alternator 1 1 3 Ammeter 1 1 4 Voltmeter 0 0 FLIGHTCONTROL SYSTEM 1 Elevator trim control electric 1 1 2 Stall warning 0 0 FUEL 1 Boost pump 1 1 2 Fuel quantity indicator wing tank 1 1 3 Fuel quantity indicator center tank 1 1 5 Fuelflow pressure indicator 1 1 LIGHT 1 Wing tip NAV lights 0 0 2 Wing tip strobe lights 1 1 NAVIGATION 1 Altimeter 1 1 2 Airspeed indicator 1 1 3 Mag direction indicator 1 1 4 OAT indicator 0 0 5 Vertical speed indicator 0 0 6 Turn and bank indicator 0 0 7 Artificial horizon 0 0 8 Directional gyro 0 0 9 Transponder 1 1 1 In some airspaces Mode S Elementary Surveillance functionality is required Page Date 19 February 2014 2 15 Section 2 Limitations Pilot s Operating Handbook US EXTRA 330LX ENGINE INDICATION 1 RPM indicator 4 Manifold pressure indicator 2 Exhaust gas temperature indicator 3 Cylinder head temperature indicator OIL 1 Oil temperature indicator 2 Oil pressure indicator FLIGHT CREW EQUIPMENT 1 Parachute rear 2 Parachute front 3 Seat belt rear 4 Seat belt front 5 Headset rear
78. 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 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 ASPENPFDAS ENCODED ALTITUDE SOURCE 917 8 The EFD1000 PFD can provide encoded altitude informatio to connected units Do not unpower the Aspen PFD when using the Garmin GTN 635 650 750 or the GTX 33 remote transponder 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
79. times See the Airman s Information Manual AIM for a detailed explanation of identification codes 9144 NORMALPROCEDURES Notapplicable 914 5 PERFORMANCE Notapplicable Page Date 19 February 2014 914 7 Section 914 Pilot s Operating Handbook US GARMIN GTX 328 Transponder EXTRA 330LX Left blank intentionally 914 8 Page Date 19 February 2014 Pilot s Operating Handbook US XTRA EXTRA 330LX Paragraph 915 1 915 1 1 915 1 2 915 1 3 915 1 4 915 1 5 915 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 915 3 Mode Selection 915 4 Code SCISCHON reiecta dera ru nen ier nd i rec du d dr n na d e 915 4 Keys for other GTX 330 915 5 UNCON DiS rir ms 915 5 Configuration Mode cte t eee 915 6 Altitude ederent n ree Gr T eu Re eS re cua en 915 6 Failure 915 6 BI pus 915 7 EMERGENCY PROCEDURES 3 25 62 915 7 IMPORTANT CODES
80. 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 must 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 ref
81. window to enter the trnasponder operation page See figures 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 19 February 2014 Pilot s Operating Handbook US Section 922 EXTRA 330LX 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 depending on location see below SELECTING ASQUAWK CODE The selected squawk code will always be in use As yo
82. with the 0 9 keys CONTRAST This page is only displayed if manual contrast mode is selected in Configuration Mode Contrast is controlled by the 8 and 9 keys DISPLAY This page is only displayed if manual backlighting mode is selected on Configuration Mode Backlighting is controlled by the 8 and 9 keys Page Date 19 February 2014 913 5 Section 913 Pilot s Operating Handbook US GARMIN GTX 327Transponder EXTRA 330LX 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 19 February 2014 Pilot s Operating Handbook US XTRA EXTRA 330LX 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 914 3 Mode Selection Keys 914 4 Code Selecon dara rune ic nid i rec du n e d d na d 914 4 Keys for other GTX 328 914 5 Funcion DiS DIAY ms 914 5
83. 0 CO st ern LO LOO o ojooo TIN CO SF LO N LO CO LO O LO gt LO mr rnm oo oo TIN tO lt CO CO Om SE lt OO IO 0 lt CO 00 lt lt lt LO CO 00 CO CO TIN OO SF N OLTIN MO Yt ONO oN ooa OIN E SE CO O CN TTT C lt SP LO LO E lt NY CO sr LO OD CO NCO s OR CO D O CN tO CO 0012 CO SE LO CO I SF CO NY CO LO OD LO MD QN COO sr O0 CN CO O Tt O0 CO ie CO SF SF SE LO CO CO Od O lt
84. 0 EFD500MFD 34022 amp 34023 1 Remote Sensor Module Aspen 910 00003 002 in 33292 33293 0 91 3 95 O RSM w o GPS 34024 amp 34025 Optional Hour Meters Flight Timer Winter FSZM 1510 01605 0 15 1 55 O Optional Clock Digital Clock Astrotech LC 2 0004 0 14 1 60 EF Optional Aerobatics Equipment 1 Aresti Card Holder Extra EA 83504 4 EA 83504 0 09 1 66 004 PG 1 Aresti Card Holder Extra EA 86504 4 EA 86504 0 09 1 66 004 PG 1 1 Sighting device Extra 8 801 30 0 55 1 60 457 90 1 Smoke System Extra 86112 9 20 0 30 Optional Electronic Accelerometer El accelerometer with TL Electronik TL 3424 EXT 32582 0 30 1 60 audio visual warning Avionics 34 amp 23 1 Becker AR 4201 00652 PG 0 67 1 54 R 1 Becker AR 6201 33041 0 85 1 54 JA 8 33kHz spacing 1 GPS COM Garmin GNC 420W 32734 PG 2 65 1 54 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 1 GPS COM Garmin GTN 635 33772 PG 2 82 1 54 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 1 60 1 GPS Antenna Garmin GA 35 32620 0 21 3 90 O 1 NAV Antenna Comant Industries 158 33035 0 16 3 90 O
85. 2 Plan a landing at the nearest airfield With extremely rapid ice build up select suitable off airport landing field 3 6 UNINTENTIONAL SPIN Refer to section 4 Normal Procedures acrobatic maneuver spin recovery 3 7 MANUAL BAIL OUT When in an emergency situation that requires abandoning the aircraft and while wearing a parachute which is at least strongly recommended for acrobatics Inform your passenger Pull mixture to lean ROD Takeoff headset Open seat belt Leave airplane to the left side Try to avoid wing and tail Reduce speed to 100 KIAS 185 km h if possible Open canopy the low pressure over the canopy in normal flight will flip the canopy full open immediately Page Date 19 February 2014 Section 3 Pilot s Operating Handbook US Emergency Procedures EXTRA 330LX 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 FAILURE In case of elevator control failure the aircraft can be flown with the elevator trim In this case trim nose up to the desired speed and control horizontal flight or descend with engine power For landing trim
86. 2636 31494 0 05 1 07 0 25 1 90 3 70 0 20 10 40 0 23 5 90 0 23 3 00 0 86 4 00 0 86 4 60 0 86 0 09 0 25 0 22 1 62 1 46 1 07 0 02 0 17 0 03 1 62 0002 19 3 30 2 12 2 90 1 03 0004 or 20 3 30 1 03 33423 31668 0 39 2 70 0 40 4 24 4 92 1 22 d gt 2 O 10 R Mooring 10 Electrics 24 Cockpit 25 Emergency Equipment R required A alternative optional Page Date 19 February 2014 Pilot s Operating Handbook US EXTRA 330LX Section 6 Weight and Balance and Equipment List 1 Strobe Nav Light RH 1 Strobe Nav Light LH 2 Strobe Power Supply 1 Landing Light LED Whelen Whelen Whelen Whelen 01 0790340 00 14V green 01 0790340 02 14V red 490 01 71125 12 32989 32990 01215 33588 0 30 0 30 0 54 0 16 1 35 1 35 1 35 0 57 R R O QTY MEM MANUFACT MODELNO PARTORP N WEIGHT ARM R INST kg A 1 Electrically Extra EA 86612 7 28 1 10 Adjustable Pedals Sys Fuel System 28 1 Elec Fuel Pump Weldon Tool B8120 M 1 10 0 04 1 Elec Fuel Pump Andair PX580 TC XT 0 47 0 04 1 Fuel Selector Allen 6 S 122 390144 0 19 0 73 R Fuel Lines in Fuselage Parker Statofl
87. 3 0 tilt 33217 0 45 1 63 A electronic 3 1 8 1 Attitude Gyro RC Allen RCA2600 3 0 tilt 33882 0 49 1 61 A electronic 3 1 8 102 0203 01 1 Slip Indicator RC Allen 444 0010 01 33529 0 08 1 68 A on RCA 2600 Reserved 1 1 Slip Skid Indicator Rieker 1040 10009 0 05 1 60 O 1 Electr Flight Display Aspen 910 00001 001 in 33846 33291 1 32 1 55 O EFD1000 34020 amp 34021 1 Configuration Module Aspen 920 00004 001 in 33846 amp 34020 0 04 1 50 O Pilot 1 Configuration Module Aspen 920 00004 002 in 33291 amp 34021 0 04 1 50 O Pro 6 12 Page Date 19 February 2014 Pilot s Operating Handbook US Ped Section 6 EXTRA 330LX Weight and Balance and Equipment List MANUFACT MODELNO PARTORP N WEIGHT ARM INST kg m 1 Remote Sensor Module Aspen 910 00003 001 in 33846 33291 0 91 3 95 O RSM w GPS 34020 amp 34021 1 RSMInstallation Extra EA 86206 10 0 19 3 95 bracket Optional Multi Function Display ASPEN 1 Electr Flight Display Aspen 910 00001 001 in 33292 33293 1 32 1 55 O EFD1000 34024 amp 34025 1 Electr Flight Display Aspen 910 00001 003 in 32956 33639 1 09 1 55 O EFD500 34022 amp 34023 1 Configuration Module Aspen 920 00004 004 in 33292 33293 0 04 1 50 O EFD 1000 MFD 34024 amp 34025 1 Configuration Module Aspen 920 00004 005 in 32956 33639 0 04 1 5
88. 330LX QTY ITEM MANUFACT MODELNO PARTORP N WEIGHT ARM R INST kg Optional add to convent eng Gauges 1 Fuel Scan Sys JPI FS 450 30611 PG 0 18 0 98 1 Fuel Flow Transducer Flowscan 201 B or FXT 201 0 09 0 02 Shadin 680501 or 680600 Fl4015 0 09 0 02 1 Engine Monitor Sys JPI EDM700 800 31530 PG 1 39 0 50 6 EGT Probe 111 0 35 0 57 6 CHT Probe JPI M 113 S Plug Gask 0 26 0 56 O 1 OAT Probe JPI 400510 0 05 1 OilTemp Probe 400500 L 0 05 0 22 1 Manifold Press Probe JPI 604010 0 05 1 55 1 RPMProbe 420809 0 05 011 1 Fuel Flow Transducer Flowscan 201 B or FXT 201 0 09 0 02 Shadin 680501 or 680600 Fl4015 0 09 0 02 Exhaust 78 1 Exhaust System 6 in 1 Gomolzig 00 606000 33891 8 48 0 39 incl silencer with 1 2 inlet outlet cooling Gomolzig EA300 606009 32153 shroud 1 Exhaust System 6 in 1 Gomolzig EA300 606000 33891 8 48 0 39 incl silencer with 1 3 inlet outlet cooling Gomolzig EA300 606024 03248 shroud for heating system Oil System 79 1 Single Oilcooler rear Aero Classics 8000353 31417 1 65 0 22 R 1 Low Temperature Extra EA 83301 300 Option 0 20 0 01 1 1 1 1 1 Breather Line Kit Starter Flyweight Starter High Torque inline Batt Charger Cable External Power Cable Smoke Filling Hose Sky Tec Sky Tec Extra Extra Extra 149 12LS 149 12NL Assy Assy
89. 4 8 4 8 1 MM m 4 8 4 8 2 E ade 48 4 8 3 Before REPRE EL EE DP P 4 8 4 8 4 Normal Landing es 4 9 4 9 ceo RUE 4 9 4 10 SHUTDONWN 12e eoe a seen eia saepe cux dace puso E ERES 4 9 4 11 B zd caas zE illie ga 4 9 4 12 ACROBATIC MANEUVERS aaraa edd R epum aaan 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 1 nein mre euni aano 4 12 Page Date 19 February 2014 4 1 Section 4 Pilot s Operating Handbook US Normal Procedures EXTRA 330LX Left blank intentionally 4 2 Page Date 19 February 2014 Pilot s Operating Handbook US Section 4 EXTRA 330LX XTRA Normal Procedures 4 0 GENERAL 4 0 1 AIRSPEEDS FOR NORMAL OPERATION CATEGORY ACROI ACROII 820 870 950 kg 1808 lbs 1918 lbs 2095105 KIAS km h KIAS km h KIAS km h Start Rotate Speed 63 117 65 120 68 126 Climb 91 169 92 170 96 178 99 183 101 187 106 196 Recommended Normal Climb Speed 100 185 105 194 110 204 Cruise 181 335 181 335 181 335 Landing Approach 84 156 89 165 93 172 onFinal 76 141 78 144 82 152 Go
90. 5 9US gal Acro tank 9L 2 3 US gal Usable fuel capacity in the system 187L 49 4US gal Usable fuel capacity for acrobatic 671 17 7US gal 1 7 OIL Maximum sump capacity 15 131 16US qt Minimum sump capacity 8 51L 905 9 Average ambientair Mil L6082 Mil 22851 temperature grades ashless dispersant grades Alltemperatures SAE 15W50 or 20W50 gt 27 80 60 gt 16 60 SAE 40 or 60 1 C til 32 C SAE 40 30 90 F Page Date 19 February 2014 1 5 Pilot s Operating Handbook US EXTRA 330LX General XTRA 1 7 OIL Cont Average ambient air Mil L6082 Mil 22851 temperature grades ashless dispersant grades 18 C til 21 C SAE 30 0 F 70 F SAE 30 40 or 20W40 18 C til 32 C 0 90 F SAE 20W50 SAE 20W50 or 15W50 SAE 30 or 20W30 lt 12 10 F SAE 20 single or multi viscosity aviation grade oils see latest issue of Textron Lyc 5 1 No 1014 1 8 LOADING Wing loading MTOW Acrobatic 111 88 62 kg m 18 15 lbs ft Acrobatic lI 81 16 kg m 16 63 lbs ft Acrobatic 76 49 kg m 15 67 lbs ft Power loading MTOW Acrobatic Ill 4 04 kg kW 6 65 lbs hp Acrobatic 11 3 70 kg kW 6 09 Ibs hp Acrobatic 3 49 kg kW 5 74 lbs hp 1 9 TERMINOLOGY Air Speeds CAS KCAS GS IAS KIAS TAS Calibrated Air Speed CAS is the same as TAS True Air Speed in standard atmospheric condition at sea level Calibrated speed in knots Ground speed
91. 6 Headset front NOTE ACROBATIC 1 seat 2 seats Ll The zeros 0 used in 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 according to FAR Part 91 Operating and Flight Rules each occupant of an US registered airplane must wear an approved parachute when performing acrobatic maneuvers Extra Flugzeugproduktions und Vertriebs GmbH considers acrobatics without wearing an approved parachute to be unsafe 2 16 Page Date 19 February 2014 Pilot s Operating Handbook US XTRA EXTRA 330LX 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 2 6 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 EMERGENCY PROCEDURE Table of Contents Page MINT PRODUCTION MSS CEPR 3 3 Gener l 3 3 General Behaviour in Emergency 3 3 AIRSPEEDS FOR EMERGENCY OPERATION nnna 3 4 OPERATIONAL CHECKLIST ete tr det toda ei diete 3 4 Engine Failure during Take off Foll
92. 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 922 3 LIMITATIONS 922 3 gris 922 5 E 922 5 922 5 MAUI 15 ONY 922 5 Flight Planning Calculation Functions 922 5 ET T 922 6 HS adie ein AA hah Re dee 922 6 EMERGENCY ABNORMAL PROCEDURES 922 6 Emergency PIOGOQUE 6S iion ccr iari istam een udo eder asset Cox 922 6 Abnormal Procedures 2 eode tue ru LE Rae pe 922 6 NORMAL PROCEDURES trennen inn EE 922 7 PERFORMANCE 922 7 WEIGHT amp CENTER OF GRAVITY cicero ern 922 8 SYSTEM DESCRIPTION 2 202 ccaer re iaa uoo cenare enm roca ran uino c nasa tru on ao 922 8 Touchscreen Key and Knob Functions 922 8 Secure 2 1 a 922 9 Selecting com nav 922 9 R
93. 7 6 Instrument Panel Front 7 8 Bbhciclim 7 8 MEATS SEAT BELTS ELE 7 8 7 8 POWERPLANT T 79 elc TET 7 9 OIl SY SUS EE 7 9 Engine InstallatlOli R 7 10 TE 7 10 r M e 7 10 IMUM c 7 10 7 10 aisi eee lE 7 10 Exhaust SySIOlTi ice canine teretes tate chad Fee E eed ad Etude e 7 10 ddl dee nae 7 10 ELECTRICAL SYSTEM 7 12 CABIN ENVIRONMENT CONTROL 7 12 Page Date 19 February 2014 7 1 7 Pilot s Operating Handbook US Description and Operation of Aircraft and Systems X TRA EXTRA 330LX Left blank intentionally 1 2 Page Date 19 February 2014 Pilot s Operating Handbook US Z Section 7 EXTRA 330LX X TRA Description and Operation of Aircraft and Systems SECTION7 DESCPRIPTION AND OPERATION OF AIRCRAFT AND SYSTEMS 7 1 THE AIRCRAFT
94. 90 0 68 1 Mech Fuel Pump Crane Lear Romec RG9080 J4A 0 57 0 30 R Ignition 1 Ignition Switch TCM 10 357200 1 00185 0 15 1 63 R 1 Magneto LH Slick 6393 32860 2 80 0 15 R 1 Magneto RH Slick 6350 02337 2 00 0 15 R 1 Slick Start Magneto Unison SS1001 32598 0 27 0 02 R Start Booster Engine Controls 1 RPM Vernier Control ACS Products Co A 750 30 1200 00113 0 71 0 82 1 Mixture Vernier Control ACS Products Co A 750 20 1080 00112 0 65 0 94 1 Throttle Control Teleflex CC330 10 33052 0 56 10 60 Conventional engine gauges Engine Instruments 1 RPM Indicator digital Horizon P100 230 33624 0 68 1 60 R max 2600 RPM 635 00 reserved 1 Oil Press Oil Temp UMA D2 OP130U 33428 0 09 1 62 R Ind 2 1 4 OT300U 01 1 Oil Temp Sender UMA 1B3A 0 08 0 11 1 Oil Press Sensor UMA N1EU150G A or 0 12 0 04 T1EU150G A 1 Manifold Pressure United Instr UI6331 H 217 03247 0 49 1 60 Fuel Flow Ind 1 Fuel Qty Ind Wing VDO 301 030 001 G 200171 0 14 1 62 1 Fuel Qty Ind VDO 301 030 002 G 00390 0 14 1 62 Fuselage Tank 1 EGT CHT Indicator UMA D2 ET1K7K 33438 0 07 1 62 R CT600J 01 1 EGT Probe UMA 2BU20 0 06 0 37 1 CHT Probe UMA 2B18 or 2B02 0 05 0 20 Page Date 19 February 2014 6 15 Section 6 Pilot s Operating Handbook US Weight and Balance and Equipment List EXTRA
95. 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 aa 917 4 Bi apape e 917 4 Placards Decals EE 917 4 EMERGENCY PROCEDURES ette dene md d 917 6 NORMAL PROCEDURES 917 6 siis ed 917 6 WEIGHT amp CENTER OF GRAVITY 917 6 SYSTEM DESCRIPTION nece nex can soos nx ade c cruor cu noon rea 917 6 Generalinis M 917 6 Pitot Obstruction Monitor Configuration 5 917 6 Databases EFD1000 500 Only 004440 10 0 nennen nnne nnne nns 917 7 RSM GPS 5 0 ET 917 8 Operation on Internal Battery ceca seeded n erecto ku 917 8 Geographic 917 9 Hazard Awareness EFD1000 PFD PRO and MFDs ONLY 917 9 Evolution Synthetic Vision Optional 917 11 Aspen PFD as Encode
96. 917 5 Page Date 19 February 2014 Section 917 Pilot s Operating Handbook US ASPEN EFD1000 500 System XTRA EXTRA 330LX 917 3 EMERGENCY PROCEDURES Not affected due to the use as a secondary instrument 9174 NORMALPROCEDURES Not affected due to the use as a secondary instrument 917 5 PERFORMANCE Notaffected 917 6 WEIGHT amp CENTER OF GRAVITY Refer to the Equipment List in Section 6 of this Handbook 917 7 SYSTEM DESCRIPTION 917 7 1 GENERAL Refer to the Aspen Pilot s Guide s as specified in paragraph 917 1 for description ofthe EFD1000 500 System 917 7 2 PITOT OBSTRUCTION MONITOR CONFIGURATION 5 ONLY The Pitot Obstruction Monitor is available only in configuration 5 EFD1000 PFD Pro and EFD1000 MFD 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 bein
97. ANING 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 19 February 2014 922 15 Section 922 Pilot s Operating Handbook US GARMIN GTN 635 650 750 XTRA EXTRA 330LX Left blank intentionally 922 16 Page Date 19 February 2014
98. C E AOE O M 910 7 Page Date 19 February 2014 910 1 Section 910 Pilot s Operating Handbook US NAT AA83 001 Intercom EXTRA 330LX Left blank intentionally 910 2 Page Date 19 February 2014 Pilot s Operating Handbook US XTRA 2 910 ntercom EXTRA 330LX 910 1 910 1 1 910 2 GENERAL 83 001 is a stereo voice activated intercom providing fullintercom capabilities for pilot and copilot Further passenger features are notused inthe configuration installed The AA83 001 also providestransmit capability for pilot and co pilotto a single COM radio or audio selector panel The AA83 001 accepts stereo music inputs from either portable or fixed entertainment systems to produce high quality stereo headset output Thestereo music audio is muted during transmit or intercom operation and when receive audio is detected permitting greater intelligibility ofincoming 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 VOX threshold 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 pi
99. D SUB 9 pins female TheTL 3424 EXT is complete weight acceleration management The instrument incorporates 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 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 19 February 2014 Pilot s Operating Handbook US EXTRA 330LX X TRA Accelerometer 451 TL 3424 EXT checks measured values at two levels for a warning and an alarm limit signalization 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 memor
100. EMPERATURE 1 Throttle REDUCE 2 Mixture ENRICH if practical 3 Airspeed INCREASE if practical 4 Land ASAP BE PREPARED FOR POWER OFF LANDING ALTERNATOR FAILURE 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 CHECK min 2500 rpm 4 Alternator switch OFF AND ON 5 ALTERNATOR circuit breaker PULL AND RESET 6 Lowvoltage monitor CHECK INDICATION If red light is off 7 Flight CONTINUE If red light illuminates again 8 Land AS SOON AS PRACTICAL Page Date 19 February 2014 3 5 Section 3 Pilot s Operating Handbook US Emergency Procedures EXTRA 330LX 3 3 FORCEDLANDINGS 3 3 1 EMERGENCY LANDING WITHOUT ENGINE POWER 1 Seat belts shoulder harnesses SECURE 2 Airspeed 90 KIAS 167 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 3 3 2 PRECAUTIONARY LANDING WITH ENGINE POWER 1 Seat belts shoulder harnesses SECURE 2 Airspeed 90 KIAS 167 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 Ignitio
101. ENT will appear in the upper left corner of the display while the IDENT mode is active VFR Pressing the VFR key sets the transponder code to the pre programmed VFR code selected in the Configuration Mode Pressing the VFR key again will restore the previous identification code FUNC Pressing the FUNC key changes the page shown on the right side of the display Displayed data includes Pressure Altitude Flight Time Count Up timer Count Down timers In the Configuration Mode steps through function pages START STOP Starts and stops the Count Up Count Down and flight timers In the Configuration Mode steps through functions in reverse CRSR Initiates starting time entry 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 selection 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 Disp
102. GE 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 current 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 OPERATIONONINTERNALBATTERY 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 and turn 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 a function ofthe input voltage to the display which can be observed via the Menu Power Settings Page 917 8 Page Date 19 February 2014 Pilot s Operating Handbook US Section 917 EXTRA 330LX XTRA ASPEN EFD1000 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 transi
103. GLIDER 1 Pilot of the glider INFORM 2 Air tow RELEASE 3 Landing PERFORM AS PRACTICAL D TOW BREAK 1 Pilot of the glider INFORM 2 Landing PERFORM AS PRACTICAL 920 4 NORMAL PROCEDURES Preflight inspection starting procedures take off procedure and the following climbing flight have to be carry out in accordance with Chapter 4 Normal procedure In addition to this procedures the following points have to be observed A PRIOR TO THE TAKE OFF A release test needs to be conducted to determine safe release operation The test shall be made on both aircraft and glider B TAKE OFF After air tow hook up the tow shall be tighened gently During the following take off and climb the maximum air tow speed of the glider must be observed C CLIMB While climbing the max C H T must be observed Towing light gliders the intial climb angle may be very steep Information of the glider pilot is recomended D RELEASE After the release of the glider a gently left handed descent shall be flown to avoid collision of glider and air tow 920 4 Page Date 19 February 2014 Pilot s Operating Handbook US Section 920 EXTRA 330LX XTRA Airtow Hook E DESCENT ANDLANDING While descending the engine temperatures shall be observed avoid overcooling Final approach should account for the air tow hanging below the aircraft flight path 920 5 PERFORMANCE The existing POH Data remain valid with the exception of TAKE OFF D
104. ISTANCE Conditions Power 2600 Rpm and full throttle mixture rich short grass dry and paved level runway no wind takeoff weight of the towing aircraft 820Kg 1808lbs Liftoff speed T O 68 KIAS 126 Km h indicated Obstacle clearance speed over 15m 508 74 KIAS 137 Km h indicated For every 5 kts 9 km h headwind the takeoff T O distance can be decreased by 5 For every 2 kts 4 km h tailwind up to 10 kts 19 km h the T O distance is increased by 1096 CAUTION All values are valid for single pilot air towing operation 820kg 1808 lbs TOW In case of an instruction flight with copilot the higher takeoff weight has to be considered The maximum permissible air towing speed of the glider needs to be observed Page Date 19 February 2014 920 5 Pilot s Operating Handbook US Section 920 EXTRA 330LX XTRA Airtow Hook 02 266 9871 60 0721 186 zee 009 WSL 3 98 Oo OF YOS WSL 001 4 01 050 7081 056 cest 79 9061 86 11 Ove 696 162 WOS 4 01 050 YLOL 698 yw 006 3 98 Oo OF 1861 1 9 286 081 496 6901 pze 991 466 voe 906 9 2 658 092 96 8711 09 699 zoz 86 1010 1 do 701 Do 0Y 2598 Do OE 257 009 WSL 09 3 89 Do OZ 2
105. LT 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 transmitting a 121 5 MHz distress signal Therefore all activations ofthe 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 19 February 2014 909 5 Section 909 Pilots Operating Handbook US ARTEXME 406 ELT EXTRA 330LX 909 8 HANDLING SERVICING AND MAINTENANCE 909 8 1 TRANSMITTER TEST 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 countas atleast 30 seconds even if the actual time is
106. LTER OF POSSIBLE WATER CHECK CLOSED CHECK FOR DAMAGE AND SECURE ATTACHMENT CHECK CHECK CHECK DRAIN FORAT LEAST 4 SECONDS TO CLEAR SUMP OF POSSIBLE WATER CHECK CLOSED REMOVE CHECK CHECK COMPLETE COMPLETE COMPLETE ADJUST ANDLOCK CLOSE AND LOCK CHECK ON OFF OFF ON ON Page Date 19 February 2014 Section 4 Pilot s Operating Handbook US Normal Procedures EXTRA 330LX 4 3 STARTINGPROCEDURES 4 3 1 COLDENGINES The following starting procedures are recommended however the starting conditions may necessitate some variation from these procedures 1 Perform pre flight inspection 2 Set propeller governor control to High RPM position 3 Open throttle approximately 1 4 travel 4 Turn boost pump ON 5 Move mixture control to FULL RICH until a slight but steady fuelflowis noted approximately 3 to 5 seconds and return mixture control to IDLE CUT OFF Turn boost 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 off the engine and determine cause of 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 Ca
107. Limitations EXTRA 330LX 2 8 ACROBATIC MANEUVERS 2 8 1 RESERVED 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 The structure is designed for full aileron control input up to 185 KIAS 343 km h in combination with 2 3 of the applicable max load factor 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 AN CAUTION Particular caution must be exercised when performing maneuvers at speeds above Va 154 KIAS 285 km h Large or abrupt rudder and elevator control inputs above this speed as well as full aileron control inputs above 185 KIAS 343 km h may impose unacceptably high loads which exceed the structural capability of the aircraft NOTE For acrobatic maneuvers see Section 4 maneuvers can be performed in upright and inverted flight attitude 6 Page Date 19 February 2014 Pilot s Oper
108. Lycoming SERVICE LETTER No L 201 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 starter magneto switch is located on the right side of the instrument panel in front of the rear seat The propeller governor monitors the RPM automatically and prevents overspeeding In the event that oil pressure is lost the propeller is automatically adjusted to coarse pitch in order to avoid overspeeding The use of 100 130 aviation grade fuel AVGAS 100 is the minimum grade recommended by the manufacturer ofthe AEIO 580 B1A engine For continuous operation 115 145 aviation fuel is the maximum grade 7 10 2 OILSYSTEM 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 For oil capacities temperatures and grades refer to Section 1 7 Page Date 19 February 2014 7 9 7 Pilot s Operating Handbook US Description and Operation of
109. MAL 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 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 19 February 2014 Pilot s Operating Handbook US Section 907 EXTRA 330LX 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
110. PanelDock AirGizmos GPSMAP 796 34175 0 27 1 60 O 1 Remote Audio Panel Garmin GMA 35 33902 PG 1 00 1 53 O Cowling 54 1 Cowling CRP Extra EA 83001 0 9 20 0 57 1 Cowling GRP Extra EA 83003 0 10 60 0 57 1 Cowling CRP incl Landing Extra EA 8E001 0 9 20 0 57 Light provision Canopy 56 Standard Canopy Extra 26301 000 LV 26301 000 VF 13 50 1 69 R Single Seat Canopy Extra EA 86411 0 86411 001 VF 13 20 1 69 a Propeller 61 1 3 Blade Propeller MT Propeller MTV 9 B C 32285 30 50 1 15 R C198 25 1 Spinner MT Propeller P 810 2 31415 0 80 1 20 R 1 4 Blade Propeller MT Propeller MTV 14 B C 33970 30 60 1 15 C190 130 1 Spinner MT Propeller P 967 31560 0 80 1 20 1 Governor MT Propeller P 880 41 32941 1 10 0 91 max 2600 RPM reserved 1 Governor Woodward A 210988 01209 1 10 0 91 A 6 14 Page Date 19 February 2014 Pilot s Operating Handbook US Section 6 EXTRA 330LX Weight and Balance and Equipment List QTY ITEM MANUFACT MODELNO PARTORP N WEIGHT ARM INST kg m A 1 Powerplant 7X Engine 1 Engine Lycoming AEIO 580 B1A 32712 191 72 0 72 R R H ENPL RT10427 4 Shock Mount Barry 94016 02 01817 1 70 0 29 Fuel Oil Sense Lines Parker Statoflex PTFE Type 101 33592 3 40 0 15 in Eng Comp Engine Fuel System 1 Fuel Injector Precision RSA 10 AD 1 3
111. RM 5 Avionic switch OFF 6 Mixture IDLE CUT OFF 7 Ignition switch OFF 8 Battery switch OFF 4 11 LEAVING THE AIRCRAFT 1 Canopy CLOSE and LOCK 2 Aircraft SECURE 3 Pitot cover ATTACH 4 Log book COMPLETE Page Date 19 February 2014 4 9 Section 4 Pilot s Operating Handbook US Normal Procedures m EXTRA 330LX 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 The high permissible load factors of the airplane may exceed the individual physiological limits of pilot or passenger This fact must be considered when pulling or pushing high g s 4 12 2 MANEUVERS CAUTION Particular caution must be exercised when performing maneuvers at speeds above Va 154 KIAS 285 km h Large or abrupt rudder and elevator control inputs above this speed as well as full aileron control inputs above 185 KIAS 343 km h may impose unacceptably high loads which exceed the structural capability
112. ROACH 1 Boost pump ON 2 Mixture SET to RICH 3 Airspeed REDUCE to approach speed 4 Propeller NOTE SET to low pitch HIGH RPM It is recommended to set the RPM to 2400 during approach and landing in order to avoid unnecessary noise In case of Go Around RPM control must be set to max RPM before applying power 4 8 3 BEFORELANDING 1 Landing approach PROCEED 2 Airspeed on final maintain 82 KIAS 152 km h 3 Elevator trim ADJUST 4 8 Page Date 19 February 2014 Pilot s Operating Handbook US Section 4 EXTRA 330LX XTRA Normal Procedures NOTE Stall speed will be MTOW 820 kg 1808 Ibs 59 KIAS 109 km h MTOW 870 kg 1918 Ibs 61 KIAS 113 km h MTOW 950 kg 2095 Ibs 64 KIAS 119 km h 4 8 4 NORMAL LANDING 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 4 9 GO AROUND Decide early in the approach if it is necessary to go around and then start go around before too low altitude and airspeed are reached Proceed as follows 1 RPMcontrol HIGH RPM Full forward 2 Throttle OPEN Take off power 3 Airspeed Minimum 102 KIAS 189 km h rotate to go around altitude 4 10 SHUTDOWN 1 Boost pump OFF 2 Landinglight OFF 3 Engine RUN for 1 min at 1000 RPM 4 Dead cut check PERFO
113. RPMINDICATOR GENERAL The EXTRA 330LX is as standard equipped with an P 1000 Digital rom indicator The following model is used P100 230 635 00 max 2600 rpm LIMITATIONS The operation limitations are not affected by the installation of the P 1000 Digital RPM indicator The face of the indicator is placarded with the unchanged engine RPM operating range Additionally the operating RPM ranges are indicated by a large green yellow and a red LED These LEDs are located on the upper right corner of the indicator face Model P100 230 635 00 max 2600RPM 2600 3500 Green EMERGENCY PROCEDURES Not affected NORMAL PROCEDURES Not affected PERFORMANCE Not affected Page Date 19 February 2014 906 3 Section 906 Pilot s Operating Handbook US Digital RPM Indicator XTRA EXTRA 330LX RPMrange Magneto Control RPM restriction Operation placard Hours Clear Trap Press and hold Operation placard Press and release 906 6 WEIGHT AND BALANCE Refer to the Equipment List in Section 6 of this Handbook 906 7 DESCRIPTION AND OPERATION OF THE SYSTEM The operation of the indicator is straight forward After power is supplied to the indicator the engine is started and the self tests are 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 dis
114. Rate of Climb at 2000 ft 610 m 2320 ft min 11 8 m s The Time to Climb from 2000 ft 610 m to 8000 ft 2438 m is acc to Fig 5 7 gt 4 0 0 9 min 2 3 1 min The Fuel to Climb from 2000 ft 610 m to 8000 ft 2438 m is gt 5 8 1 4 Liters 4 4 Liters 1 2 US Gal CRUISE Cruise Altitude and Power Setting should be determined for most economical fuel consumption and several other considerations In an altitude of 8000 ft 2438 m and a Power Setting of 65 96 a Fuel Consumption of 52 L H 13 7 US Gal H and 3 25 NM L 12 3 NM US Gal can be obtained by Fig 5 9 RANGE AND ENDURANCE Fig 5 8 presents Range and Endurance values for a T O Weight of 950 kg 2095 Ibs including fuel for warm up and Take Off from SL max continuous Power climb to cruising altitude and a reserve of 21 liter 5 5 US Gal for 45 minutes with 4596 Power 5 5 liters 1 45 US Gal unusable fuel is taken into account Forthe sample problem appr Total Fuel 171L 45 1 US Gal Warm Up amp T O 5L 1 3 US Gal Reserve 211 5 54 US Gal Unusable Fuel 5 5L 1 45 US Gal Usable Fuel 139 5L 36 8 US Gal Range 415 NM 768 km Endurance 2 49 HRS 5 4 Page Date 19 February 2014 Pilot s Operating Handbook US 25 Section 5 EXTRA 330LX XTRA Performance 5 2 ISA CONVERSION ISA Conversion of pressure altitude and outside air temperature TEMPERATURE F 80 40 0 40 80 120 16 15 oO 14
115. T 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 19 February 2014 Pilot s Operating Handbook US Section 916 EXTRA 330LX 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 CENTER OF GRAVITY Refer to the equipment list in Section 6 of this Handbook SYSTEM DESCRIPTION KEY AND KNOB FUNCTIONS LEFT HAND KEYS AND KNOBS The COM power volume knob controls unit power and communications radio volume Press
116. 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 atpower up and require a pilot action to acknowledge Database information can also be accessed via the main menu Page Date 19 February 2014 917 7 Section 917 Pilot s Operating Handbook US ASPEN EFD1000 500 System XTRA EXTRA 330LX 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 RSM GPS USA
117. To prevent flutter rudder and elevator are mass balanced The balance weight for the rudder is installed in the nose of the rudder horn while the balance weights for the elevator are mounted near the outside elevator tips and in the center position 7 4 Page Date 19 February 2014 Pilot s Operating Handbook US Section 7 EXTRA 330LX X TRA Description and Operation of Aircraft and Systems 7 5 FLIGHT CONTROL SYSTEM 7 5 1 PRIMARY CONTROL SYSTEM The EXTRA 330LX is standard equipped with full dual primary flight controls including front and rear sticks and adjustable rudder pedals The primary control surfaces are operated through a direct mechanical linkage 7 5 2 LONGITUDINAL FLIGHT CONTROL SYSTEM Front and rear sticks are interconnected by a push rod inside the torque tube From there the control movements are transferred to the elevator by two additional push rods 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 adjustable and operate the rudder through a cable system Springs keep the cables under tension when they are not operated 7 5 5 SECONDARY CONTROL The elevator trim tab is actuated by an electric tr
118. US External Power EXTRA 330LX Left blank intentionally 905 2 Page Date 19 February 2014 Pilot s Operating Handbook US Z Section 905 EXTRA 330LX External Power 905 905 1 905 2 905 3 905 4 EXTERNAL POWER GENERAL The EXTRA 330LX 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 cool down between attempts Repeat 6 times 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 Set propeller governor control to High RPM position 3 4 5 Open throttle approximately 1 4 travel Battery switch OFF Alternator switch OFF CAUTION Risk of d
119. ach a landing light can be integrated in the RH lower cowling 919 2 LIMITATION Nochange 9193 EMERGENCY PROCEDURES Nochange 919 4 NORMALPROCEDURES change 919 5 PERFORMANCE change 9196 WEIGHT AND BALANCE Refer to the Equipment List in section 6 of this Handbook 919 7 DESCRIPTION OF THE SYSTEM The landing light is controlled by the LANDING LIGHT switch on the right instrument panel The system is protected by the LANDING LIGHT circuit breaker 9 9 N 9 o 9 A OFF LANDING LIGHT 4 Gol O LIGHT Ji o o o 75559 09 9 00900 Page Date 19 February 2014 919 3 Section 919 Pilot s Operating Handbook US Landing Light XTRA EXTRA 330LX 919 8 HANDLING SERVICING AND MAINTENANCE Nochange 919 4 Page Date 19 February 2014 Opening Handbook US XIRA SECTION 920 AIRTOW HOOK Table of Contents Paragraph Page 920 1 GENERALE tet tates eiit eet date cut 920 3 920 2 LIMITATIONS cia 920 3 920 3 EMERGENCY 04 44 0 0 a 920 4 920 4 NORMAL PROCEDURES arani nE EEA uon 920 4 920 5 dae hiuc
120. activated automatically after an aircraft accident or forced landing with high G force turn additionally the remote switch in the rear panel to the ON position After sighting rescue aircraft Switch the remote switch to the ARM position to prevent radio interference Attempt contact with rescue aircraft with the radio transceiver set to a frequency of 121 5 MHz If no contact is established switch the remote switch to the ON position immediately If the function of the remote switch is in doubt proceed as follows Remove quick pins from the backrest adjustment and swivel the backrest forward to get access to the ELT unit Usethe unit master switch at the ELT unit analogously FUNCTION CHECK OF THEELT Ifthe aircraft receiver is operable listen on 121 5 MHz for ELT transmission Ensure thatthe antenna is clear of obstruction 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 19 February 2014 Pilot s Operating Handbook US Section 909 EXTRA 330LX XTRA ARTEX ME 406 ELT 9097 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 cover behind the cockpit and a remote switch with LED indication located on the instrument panel The sw
121. 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 parameters 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 19 February 2014 Pilot s Operating Handbook US Section 914 EXTRA 330LX GARMIN GTX 328 Transponder 914 2 LIMITATIONS Notapplicable 914 3 EMERGENCY PROCEDURES 914 3 1 IMPORTANT CODES 7600 Loss of communications 7500 Hijacking 7700 Emergency All secondary surveillance radar sites are ready to receive this code at all
122. aed 909 5 909 8 HANDLING SERVICING AND MAINTENANCE _ 909 6 909 8 1 Transmitter TeSt 909 6 909 8 2 Self TESI dece ta pero educ si ET ONE 909 6 Page Date 19 February 2014 909 1 Section 909 Pilots Operating Handbook US ARTEXME 406 ELT EXTRA 330LX Left blank intentionally 909 2 Page Date 19 February 2014 Pilot s Operating Handbook US Section 909 EXTRA 330LX XTRA ARTEX ME 406 ELT 909 1 GENERAL To improve the passive security the EXTRA 330LX can be equipped with an optional Emergency Locator Transmitter ARTEX ME 406 Inthe eventof acrash the ME 406 activates automatically automatic fixed configuration and transmits the standard swepttone on 121 5 MHz lasting until battery power is gone 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 buzzer beeps and the panel LED pulses
123. aken 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 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 aircraft to ATC A triangle on the left next to the code signals the transponder replies SQUAWK IDENT After a squawk ident request from ATC press Ident button IDT D briefly This transmits an additional special pulse SPI for approx 18 seconds which enables the aircraft to be clearly identified on the radar screen of the controller Idt appears in the bottom line of the LC display during this time TEST 1 Th
124. 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 13 KEYS FOR OTHER GTX 328 FUNCTIONS IDENT Pressing the IDENT Key activates the Special Position Identification SPI Pulse for 18 seconds identifying your transponder return from others on the air traffic controller s screen The word IDENT will appear in the upper left corner of the display while the IDENT mode is active VFR Sets the transponder code to the pre programmed VFR code selected in Configuration Mode this is setto 7000 atthe factory Pressing the VFR Key again restores the previous identification code FUNC Changes the page shown on the right side ofthe display Display data includes Pressure Altitude Flight Time Count Up and Count Down timers Also displays Contrast and Display if manual control and backlighting is selected in the installation configuration START STOP Starts and stops the Count Up Count Down and Flight timers CRSR Initiates starting time entry for the Count Down timer and cancels transponder code entry CLR Resets the Count Up Count Down and Flight timers Cancels the previous keypress during code selection and Count Down entry Returns cursor to the fourth code digit within five seconds after entry 8 Reduces Contrast and Display Brightness when the respective fi
125. amage 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 Movemixture 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 19 February 2014 905 3 Section 905 Pilot s Operating Handbook US External Power EXTRA 330LX yN 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 Battery 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 polarit
126. ance Pilot s Operating Handbook US EXTRA 330LX CLIMB PERFORMANCE 5 6 uwy 0 944 481 een SVIM 26 S6 86 101 0 4 4698 581 981 4o9 sq 991 voz 481 9861 9605 25004 201 0 0Z OSL 008 048 006 0S6 851 51 851 951 851 0 00 008 0021 0091 0002 00v2 008c 002 4 0 1100091 2 130001 3200021 v 1100001 g 110008 110009 8 3000 01 430002 15 21 vl OZS L VSI 0008 0 4 0002 Wd SIM uidi 0092 inj 204 v481 Dy 098 Page Date 19 February 2014 Section 5 Pilot s Operating Handbook US EXTRA 330LX XTRA Performance TIME TO CLIMB FUEL TO CLIMB 5 7 1 98 186 97r OLE 902 691 0281 91 vi 21 OL 8 9 v OL 591 991 OSL 5017481 es o 597 600 5961 2 0 5 4 1H9I3M 0S6 006 SSS CLS sn 91 t t uiu 51 u 0008 lt lt YSI 11 0002 597 481 098 8INTTO OL LIV LHOI3M 48 9945 1995 058 008 OSL 004 VSI d33dS LV 1LNOO 02 SNOLLIINOO ulu 3 841129 OL AWIL Page Date 19 February 2014 5 10 Section 5 Performance
127. ating Handbook US Section 2 EXTRA 330LX XTRA Limitations Maneuvers Recommended entry speeds IAS Symbol Remarks min knots km h knots km h Segment horizontal Line Vs VNE 45 climbing 80 148 VNE 90 up VNE 45 Vs VNE e reduce throttle 90 diving Vs VNE if reduce throttle 1 4 Loop climb 100 185 190 352 100 185 190 352 A Stall turn 100 185 190 352 80 148 185 343 X full deflection Snap roll 80 148 140 259 eH tail slide 100 185 190 352 a i Spin Vs Inverted spin Vs Knife edge gt 150 278 e e lt 105 Inverted Flight gt Vs 190 352 S lt 4 min 2 9 LOADFACTOR 2 9 1 RESERVED 2 9 2 ACROBATIC FLIGHT Category MTOW 820 kg 1808 Ibs 10g 10g for 1 seat occupied Category Il MTOW 870 kg 1918 Ibs 8g 8g for 2 seat occupied Category III MTOW 950 kg 2095 Ibs 69 for 2 seat occupied Page Date 19 February 2014 2 7 Section 2 Pilot s Operating Handbook US Limitations XTRA EXTRA 330LX 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 OPERATION LIMITS Only VFR f
128. b 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 for the 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 19 February 2014 Pilot s Operating Handbook US Section 922 301 XTRA GARMIN GTN 635 650 750 Squawk Code Window Squawk Code Active Backspace Key VFR Squawk Transponder Code 1200 Key Selection ackspace p R 1 200 5 d Annunciation 0 2 3 Active XPDR 4 4 ENR XPQR Code Psl Erzer 2 Enter Key Context Sensitive Mode Key Instructions for Rotary Knob Figure 3 GTN 6xx XPDR Operation 922 7 2 SECURE DIGITAL CARD Secure Digital SD card is used to load and store various types of data and for various database updates Ensurethe 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 standby frequency in blue is active for editing Turn the larg
129. 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 19 February 2014 Opening Handbook US XIRA SECTION 919 LANDING LIGHT Table of Contents Paragraph Page 919 1 GENERALE eevee ace cep n retouche imde ave 919 3 919 2 LIMITATION etTS 919 3 919 3 EMERGENCY 2 22444 4 44 2 919 3 919 4 NORMAL PROCEDURES nanana annn enr oce Doc Ya nm mu c Yn n aon Dn cen vue Y 919 3 919 5 ade bl e cct evils 919 3 919 6 WEIGHT AND BALANCE oic nenne accru neun n en ccn cauaa nene ccr ava v akuten OOo 919 3 919 7 DESCRIPTION OF THE SYSTEM ni se nuns 919 3 919 8 HANDLING SERVICING AND MAINTENANCE nnaman nne 919 4 Page Date 19 February 2014 919 1 Section 919 Pilot s Operating Handbook US Landing Light XTRA EXTRA 330LX Left blank intentionally 919 2 Page Date 19 February 2014 Pilot s Operating Handbook US Section 919 EXTRA 330LX XTRA Landing Light 919 LANDING LIGHT 919 1 GENERAL To improve the visibility of the aircraft during landing appro
130. book US EXTRA 330LX XIRA Section 916 GARMIN GNC 420W GNS 430W 916 1 GENERAL The Garmin 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 Comm Freq Dimming Flip Flop Power and Com Volume Squelch Data Cards Nav Radio Volume Nav Radio Flip Flop Large Knob pM Le Com VLOC ns Freq MHz Terrain Flight Small Knob Phase and Com VLOC GPS Integrity Freq kHz Annunciator Nav Freq Com Freq Graphic Moving Window Navigation Source GPS VLOC or GPS PTK Window Display and Direct To Key Navigation Info Range Keys Menu Key Enter Key Function and Page Number Large Knob Small Knob Cursor Press to activate Paghe Pian Procedure Key Message Key This supplementis written for main software version 3 00 and GPS software version 3 0 andis not suitable for earlier software versions Some differences in operation may be observed when comparing the information in this supplement to later software versions Verify the information herein with the 400W Series Pilot s Guide amp Reference P N 190 00356 00 applicable Revision
131. capacity indicator THE REMAINING FUEL IN LEVEL FLIGHT CANNOT BE USED SAFELY WHEN INDICATOR READS ZERO On the rear instrument panel beneath the acro amp center tanks 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 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 19 February 2014 Pilot s Operating Handbook US Section 2 EXTRA 330LX 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 i gt UNLOCK e near canopy locking handles of each cockpit qp VENT Near the eyeball type adjustable vents CAUTION Particular caution must be exercised when performing maneuvers at speeds above 154 KIAS 285 Large abrupt rudder and elevator control inputs above this speed as well as full aileron control inputs above 185 KIAS 343 km h may impose unacceptably high loads which exceed the structural capability of the aircraft In both cockpits WARNING SOLO FLYING FROM REAR SEAT ONLY In front instrumental panel
132. d Altitude 917 12 HANDLING SERVICING AND MAINTENANCE enne nnns 917 12 Page Date 19 February 2014 917 1 Section 917 Pilot s Operating Handbook US ASPEN EFD1000 500 System XTRA EXTRA 330LX Left blank intentionally 917 2 Page Date 19 February 2014 Pilot s Operating Handbook US Section 917 EXTRA 330LX XTRA ASPEN EFD1000 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
133. d 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 19 Februar 2014 902 3 Section 902 Pilot s Operating Handbook US Electric Pedal Adjustment XTRA EXTRA 330LX 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 160 mm 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 10 sec FWD UGU BACK BACK LEFT RIGHT PEDAL PEDAL O 010101010 ADJUST Figure 1 Switch Circuit Breaker Loca
134. de or if the cursor is moved so far that it can no longer be seen in the display field or the identification Switch is pressed in the ON or ALT mode the code currently set is switched active NOTES Whilst settings are taking place the transmission branch of the transponder is inhibited to prevent unintentional transmission If only two digits were named by e g Squawk alpha 64 then a zero is to be used for positions three and four i e 6400 The last used code is stored in each case andis also activated when the transponder is switched on SPECIAL VFR CODINGS Two user specific codes can be stored and activated on the transponder Page Date 19 February 2014 911 5 Section 911 Pilot s Operating Handbook US BECKER ATC 4401 Transponder EXTRA 330LX 1 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 Pressthe VFR1 push button F orthe 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 storage operation is aborted NOTE If one of the two buttons F or G is pressed without the STO button having been pressed beforehand then the stored code allocated this button appears in the code display and is switchedto active after 3 seconds can be changed inthe config
135. der B for selection In selection mode additional information is displayed in the bottom line of the display Some of the data are editable some are read only VFR 4096 code presetting editable Al Aircraft Identifier fixed read only from address module an be replaced by Tail Number FN no valid Al is stored is displayed EN Flight Number or editable Company Call Sign can be replaced by AI fixed byselecting Al DEF AA Aircraft Address fixed read only from addressmodule 24 bit ICAO unique number for each aircraft MA Airspeed fixed read only from address module AT Aircraft Type fixed read only from address module CFG Configuration available in SBY mode only INS Installation setup available in SBY mode only protected by password AIRCRAFT IDENTIFICATION AI OR FN With flight plan The definition out of the flight plan e g Flight Number or Company Call Sign Without flight plan VFR Tail Number Call Sign The indication of 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 andturningthe rotary encoder B The default value for Al is the Tail Number of the aircraft and is stored in the Address Module If a flight plan exists it has to be checked which Al has to be used If a Flight Number is assigned it has to be en
136. e 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 strap All belts are adjustable As each lap belt features a single point release they are redundant for safety during aerobatic maneuvers If one release is opened unintentionally the second one guarantees full safety For safe operation the releases are arranged in a way that one has to be closed to the right side the other one to the left During acrobatic maneuvers the seat belt system should be tightened firmly 7 9 CANOPY The canopy is manufactured in one section and can be manually operated by interior locking handles located on the left side on the canopy To 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
137. e following different tests are integrated in the transponder or canbe triggered at the transponder Automatic switching on test in which the display E is flashing with all digits for 3 seconds The unit is subject to a self test in this time Page Date 19 February 2014 911 7 911 Pilot s Operating Handbook US BECKER 4401 Transponder EXTRA 330LX 2 Apermanenttestruns inthe background ofthe 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 and VFR2 button are pressed simultaneously At this test all segments must flash into display E as long as the buttons are pushed Additional the transmitter and evaluation are tested on correct function in the SBY ON and ALT modes 4 Incase of a failure appears the report e g E10 in the top line of the display Switch OFF the transponder at such E fault indications 911 1 8 CONFIGURATION MODE The configuration Mode is used to 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
138. e load are used a breaking piece weak links of max 850 kp 1875 lbs must be interconnected For a safe air towing the following points must be observed 9 Max Takeoff Weight 820 kg 1813 Ibs 870 kg 1924 Max Empty Weight 701 kg 1546 105 665 ETT 1466 Ibs Min Air Towing Speed 69 KIAS 128 km h 72 72 KIAS 133 km h 133 km h Best Air Towing Speed 76 80 KIAS 78 82 KIAS 141 148 km h 144 152 km h NOTE 2 seats only in case of an instruction flight 1 Maximum air towing speed maximum permissible air towing speed of the glider 2 The maximum permissible cylinder head temperature is 465 red line 3 Interior mirror mounted For the location of the yellow release knob the following placard has to be attached in the near of the knob AIR TOW Page Date 19 February 2014 920 3 Section 920 Z Pilot s Operating Handbook US Airtow Hook EXTRA 330LX 920 3 EMERGENCY PROCEDURES A ABORTED TAKE OFF 1 Pilot of the glider INFORM 2 Throttle IDLE 3 Mixture IDLE CUT OF 4 Brakes APPLY AS PRACTICAL B ENGINE FAILURE IMMEDIATELY AFTER TAKEOFF Stall speed 64 KIAS 119 km h 1 Pilot of the glider INFORM 2 Air tow RELEASE 3 Airspeed 90 KIAS 167 km h 4 Mixture IDLECUTOFF 5 Fuelshutoff valve OFF 6 Ignition switch OFF 7 Master switch OFF 8 Forced landing PERFORMAS PRACTICAL C EXCESSIVE CLIMB OVER BY THE TOWING
139. e 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 19 February 2014 922 9 Section 922 Pilot s Operating Handbook US GARMIN GTN 635 650 750 XTR A EXTRA 330LX Active Transponder Active Selection Transponder Audio XPDR NAY Transponder Control 1 IDENT 117 95 Code Key Code MON 1200 Display and Mode intercom Eg R 108 05 Reply Annunciation Squawk Code Backspace Key VFR Squawk Code 1200 Key Squawk Code Window Numeric Keypad Mode Standby Altitude Reporting Green Bar Indicates Active Condition Enter Key Context Sensitive Transponder Instructions for Mode Keys Rotary Knob Figure 4 GTN 750 XPDR Operation 922 7 4 REMOTE TRANSPONDER OPERATION Optionally a remote transponder GTX 33 can be controlled viathe GTN 635 650 750 unit Touch the transponder
140. e system on ground is only allowable for a brief system test 6 Wearing a parachute is strongly recommended Operating Markings amp Placards SMOKE OIL ET External Next to the quick On switch of connector at the fuselage bottom the throttle lever On instrument panel above control switch row On instrument panel SMOKE below control switch row Lowe For SINGLE PUMP SYSTEM On instrument panel above circuit breaker row __ On instrument panel 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 19 February 2014 907 3 Section 907 Z Pilot s Operating Handbook US Smoke System XTRA EXTRA 330LX FIRE IN FLIGHT 1 Switch SMOKE ARM OFF CAUTION If the fire after the smoke system is shut off will not extinguish proceed as follows 2 Mixture 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 NOR
141. e 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 19 February 2014 Pilot s Operating Handbook US Section 910 EXTRA 330LX XTRA NAT AA83 001 Intercom The copilotwill 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 no possibility of lost communication because of a lack of pilot action Note that the 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 amulti 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
142. e 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 obstructions 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 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
143. ed 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 ADAHRS solution will automatically restore once the magnetic vector can again be resolved Within aregion 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 19 February 2014 917 9 Section 917 Pilot s Operating Handbook US ASPEN EFD1000 500 System XTRA EXTRA 330LX 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
144. eing a fail safe design consists of carbon roving caps combined with CRP webs Core foam is a PVC foam The wing shell is built by a Honeycomb sandwich with CRP laminates Wing box ribs are made of carbon fiber composite with honeycomb core The ribs in the nose section are made of wood 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 The ailerons are supported at four points in spherical bearings In addition the aileron tip has ashielded horn balance The hinge line of the ailerons is positioned 25 of the aileron chord Furthermore the ailerons are equipped with spades to decrease pilot s forces The aileron control push pull rods are connected to the aileron atthe second bearing point in span wise direction To prevent flutter the ailerons are mass balanced at the leading edge of the shielded horn 7 4 The EXTRA 330 possesses acruziform empennage with stabilizers and moveable control surfaces The rudder is balanced aerodynamically at the tip Spars consist of PVC foam cores CRP caps and CRP laminates The shell is built using honeycomb sandwich with CRP laminates Deviating from the other control surfaces the spar webs of the surfaces of the elevator is built by CRP On the R H elevator half a trim tab is fitted with two hinges The control surfaces are mounted in spherical bearings exception trim tab
145. elds 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 FUNCTIONDISPLAY PRESSURE ALT Displays the altitude data supplied to the GTX 328 in feet hundreds of feet i e flight level or meters dependent upon installation configuration FLIGHT TIME Timer start is configured as either Manual or Automatic When Manual displays the Flight Time controlled by the START STOP and CLR keys When Automatic the timer begins when take off is sensed Page Date 19 February 2014 914 5 Section 914 Pilot s Operating Handbook US GARMIN GTX 328 Transponder XTRA EXTRA 330LX 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
146. emote transponder operation 922 10 Remote audio panel operation GTN 750 922 12 Powering up the GTN 635 650 750 icit atc e sire ea 922 14 maeta RT dE VAN 922 15 Ground Operation P 922 15 Traffic Display Optional esternir pte ertet erede epe ru tur aser oe tad ended 922 15 SCREEN CLEANING Rm 922 15 Page Date 19 February 2014 922 1 Section 922 Z Pilot s Operating Handbook US GARMIN GTN 635 650 750 XTRA EXTRA 330LX Left blank intentionally 922 2 Page Date 19 February 2014 Pilot s Operating Handbook US Section 922 EXTRA 330LX XTR A 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 of the 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 Squelch On Off Function and NAV ID On Off Keys Home Display GARMIN HOME Key Photo Sensor SD Card Message LE Direct To Key Annunciation And Key 21 Large and Small Locking Knobs Scre
147. enter tank Trim switch different positions possible PTT switch Fuel quantity center tank Fuel quantity wing tank Circuitbreaker Switches Position Item Fig 2 Alternator warning light incl press to test feature Battery switch red cap Alternator switch red cap Boost pump switch Strobe light switch NAV light switch Reserved Trim circuit breaker 12 V circuit breaker Starter circuit breaker Alternator circuit breaker Boost pump circuit breaker Strobe light circuit breaker NAV light circuit breaker Instruments circuit breaker COM circuit breaker Transponder circuit breaker Avionic switch circuitbreaker This list may modified by the minimum equipment requirements of individual certifying authorities Page Date 19 February 2014 7 7 7 Neu Pilot s Operating Handbook US Description and Operation of Aircraft and Systems X TRA EXTRA 330LX 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 LANDINGGEAR 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 submerged airintake for brak
148. erefore 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 the Aspen 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 21 PLACARDS AND DECALS Next the EFD PFD System circuit breaker MFD Next to the EFD MFD System circuit breaker above the EFD display head s 917 4 Section 917 ASPEN EFD1000 500 System Pilot s Operating Handbook US EXTRA 330LX XTRA JOSUBS Sd9 JOSUuaS WSH uoNeINBWUOD WD s NSN INSM x x 1 jeuondo 000 243 JO Qa 000 i 9001 gt A y y INO jieuondo 00S 933 INO eoJnog 5 5 OU yelut IEIS PEON Figure 1 Equipment Configuration
149. erence 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 the basis for maneuvering and must not be used for navigation 917 10 Page Date 19 February 2014 Pilot s Operating Handbook US Section 917 EXTRA 330LX XTRA ASPEN EFD1000 500 System 917 7 8 EVOLUTION SYNTHETIC VISION OPTIONAL NOTE Navigation or maneuvering based solely on the EFD1000 or MFD500 Synthetic Vision background display and associated Terrain Warning System TWS is not authorized Pilotin 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 Sonalert installed 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 Sys
150. erridden by the active condition Idle Functions that are not active but still available for use AUTOMATIC FAIL SAFE Inthe event of apower failure automatic fail safe operation willbe activated Fail safe mode routes the pilot s phones mic audio and mic PTT directly to the COM radio During transmit mode the pilot micis 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 has 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 19 February 2014 Pilot s Operating Handbook US XTRA EXTRA 330LX 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 nnne nenne nennen nnns 911 4 Switching on the unit pre f
151. essful 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 TheCBIT Continuous Built in Test works as follows Thecontinuous BIT acts as a kind of watchdog during operation Negative results ofthe CBIT are indicated on the display with FAILURE In this case the transponder may be not switched into ON or ALT mode display indication of operating mode set to SBY if any failure was found 3 ThePBIT Power on Built in Test works as follows The XPDR has apower on after switching on During the PBIT any action from other switches are not accepted 912 6 Page Date 19 February 2014 Pilot s Operating Handbook US Section 912 EXTRA 330LX BECKER BXP 6401 Transponder During the PBIT the in the SBY mode butthis is notindicated on the display The operating mode indication on the display starts immediately after finalisation of the PBIT Negative results are indicated 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 and rotate enco
152. ex PTFE Type 124 33315 1 66 0 70 R 1 2 Fuel Cont Probe Wing VDO 226 801 015 001 4006 0 12 0 89 1 Fuel Cont Probe VDO 224 011 020 372 01920 0 20 044 Fuselage Tank Landing gear 32 2 Main Wheel Tires Goodyear 505C61 B 02323 3 90 0 33 R 5 00 5 6PR 2 Tube Goodyear 302 013 400 FF0016 2 Main Wheel Tires McCreary 06 08200 A 5 00 5 6PR 2 Tube McCreary 06 08300 A 2 Wheel assembly Cleveland 199 197 02497 6 40 0 33 2 Master Brake Matco MC 4E 0001 0 55 0 15 R Oylinders front 2 Master Brake Matco 4 0001 0 55 1 11 Oylinders rear 1 Tail Wheel 6 Assy Special Products 32477 NB 1 28 5 28 R Soft Aviation Inc 1 Tail Wheel 5 Steerable Extra EA 53201 7 53201 007 VB 0 90 523 L R Wheel fairing CRP Extra EA 53102 301 0 33 2 50 1 Brake Fluid Reservoir ACS A 315 02889 0 20 0 04 Lights 33 Navigation Flight Instruments Avionics 34 1 Accelerometer 3 1 8 Kollsman Pioneer AN 5745 FI3001 0 40 1 60 R Bendix Jaeger Century 1 Accelerometer 2 1 4 Kollsman Pioneer AN 5745 01206 0 30 1 60 Bendix Jaeger Century 1 Magnetic Compass SIRS Navigation Ltd PG2A 33085 0 13 1 62 R 1 Magnetic Compass Airpath C 2300 00189 0 25 1 62 1 Airspeed Indicator United Instr UI8030 B 882 32811 0 32 0 65 O front kts 1 Airspeed Indicator United Instr UI8030 B 896 33630 0 32 0 65 front kts km h Page Date 19 February 2014 6 11 Section 6
153. f 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 ATC to transmit a code e g squawk alpha 6426 2 Using the rotary switch and the button C set the 4 digit code requested by as follows Using switch C move the cursor tothe particular digit Digits 0 to 7 can then be set using the 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 7500 Hijack code Aircraft is subject to unlawful interference 7600 Loss of communications 7700 Emergency 7777 Military interceptor operations Never squawkthis code 0000 Military use Not enterable Page Date 19 February 2014 912 5 Section 912 bung Pilot s Operating Handbook US BECKER BXP 6401 Transponder EXTRA 330LX 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 tran
154. g 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 will fail the attitude solution posta red X in place of the attitude and heading information and present 917 6 Page Date 19 February 2014 Pilot s Operating Handbook US Section 917 EXTRA 330LX XTRA ASPEN EFD1000 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 330LX doesn t feature pitot heating system So the 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 Onc
155. gations It operates on radar frequencies receiving ground radar interrogations at 1030 MHz and transmitting a coded response of pulses to ground based radar on a frequency of 1090 MHz The 4401 is equipped with IDENT capability that activates the Special Position Identification SPI pulse NOTE The ATC 4401 owner accepts all responsibility for obtaining the proper license before using the transponder Refer to Becker Pilot s Guide Page Date 19 February 2014 911 3 911 BECKER 4401 Transponder Pilot s Operating Handbook US EXTRA 330LX CONTROLS ANDINDICATORS 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 Ais switched ALT position Mode 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 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 idt appears in the bottom line of the LC display 2 line LC display Code indication top line Codes from
156. gine power 90 KIAS 167 km h Landing without engine power 90 KIAS 167 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 ENGINEFAILUREIMMEDIATELY AFTERTAKE OFF Stall speed 64 KIAS 119 km h 1 Airspeed 90 KIAS 167 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 90 KIAS 167 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 19 February 2014 Pilot s Operating Handbook US Section 3 EXTRA 330LX 3 2 4 3 2 5 3 2 6 LOSS OF OIL PRESSURE 1 Positive g Apply If oil pressure is not regained then 2 Airspeed 90 KIAS 167 km h 3 Throttle REDUCE AS REQUIRED 4 Engine oil temperature OBSERVE INDICATION 5 Land ASAP BE PREPARED FOR POWER OFF LANDING AX WARNING If oil pressure drops to 0 psi kPa the propeller pitch changes automatically to coarse high pitch with a corresponding decrease in RPM HIGH OIL T
157. h Continue 922 7 7 MAP PAGE 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 SCREENCLE
158. he 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 placed on a balance and jacked to such a position that the fuselage reference line upper fuselage stringer tube is horizontal There are two engine hoists provided on the top of the engine which can be used to lift the airplane with crane Tail wheel resting on ground 8 4 Page Date 19 February 2014 Pilot s Operating Handbook US XTRA EXTRA 330LX Section 9 901 902 903 904 905 906 907 908 909 910 911 912 913 914 915 916 917 918 919 920 921 922 Jb E EB E E 9 SUPPLEMENTS Doc No EA 0E701US 1 Table of Contents Pages 1 eat 4 p Steerable Wheel cene cccenicce cancer cenie sene reete dn nen eras 4 p Electric Pedal Adjustment 4 Cabin Heating System 4 p Accelerometer TL 3424 EXT 6 p angue 4 p Digital RPM Indicator ooi Icone Leere nitri e onec ranae orn x aude c eene 6 p Smo
159. he 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 X1 W2 x X2 CG position Reference Firewall plane DUDEN 2 _ Page Date 19 February 2014 Section 6 Weight and Balance and Equipment List Pilot s Operating Handbook US EXTRA 330LX 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 XG Wo Wn Wo x Xo Wn x Xn CG position W 6 2 1
160. ht level J VFR Push button Activates VFR code in the upper row of the display 912 1 2 SWITCHING ONTHEUNIT PRE FLIGHT CHECK 1 Checkthat the circuit breaker is set and switch on the aircraft power supply 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 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 selector A 912 4 Page Date 19 February 2014 Pilot s Operating Handbook US Section 912 EXTRA 330LX 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 o
161. ifferent 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 19 February 2014 Opening Handbook US XIRA SECTION 905 EXTERNAL POWER Table of Contents Paragraph Page 905 1 GENERAL 905 3 905 2 LIMITATIONS iiss 905 3 905 3 EMERGENCY PROCEDURES 2 2 4 1 1 905 3 905 4 905 3 905 5 PERFORMANCE gt gt 2 25 905 4 905 6 WEIGHT AND BALANCE pma kin mni anao ma cna 905 4 905 7 DESCRIPTION OF THE 5 5 22242 4 4 411 1 905 4 905 8 HANDLING SERVICING AND MAINTENANCE eese nnne 905 4 Page Date 19 February 2014 905 1 Section 905 Z Pilot s Operating Handbook
162. ight should not exceed 10 seconds WARNING 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 19 February 2014 Pilot s Operating Handbook US Section 2 EXTRA 330LX XTRA Limitations 2 5 PROPELLER MT Propeller Entwicklung GmbH Federal Republic of Germany a Standard MTV 9 B C C 198 25 3 blade constant speed b Alternative MTV 14 B C C190 130 4 blade constant speed Maximum rotational speed Take Off and Maximum Continuous 2600 rpm 2 6 WEIGHT LIMITS Max allowed empty weight Acrobatic category III 742 kg 1636 105 Acrobatic category Il 662 kg 1460 105 Acrobatic category 686 kg 1513 105 Max allowed T O weight Acrobatic category III 950 kg 2095 105 Acrobatic category Il 870 kg 1918 105 Acrobatic category 820 kg 1808 105 Max allowed landing weight 950 kg 2095 Ibs 2 7 WEIGHT AND C G ENVELOPE Vertical reference fire wall Horizontal reference upper longerons in cockpit 2 7 1 RESERVED 2 7 2 ACROBATICFLIGHT Max T O Weight forward C G rear C G 950 kg 2095 Ibs 67 1 cm 26 4 84 1 cm 33 1 below Page Date 19 February 2014 2 5 Section 2 2 Pilot s Operating Handbook US
163. ill remove the cursor and cancel data entry restoring the previous code You may press the CLR key up to five seconds after code entry is complete to return the cursor to the fourth digit The numbers 8 and 9 are not used for code entry only for entering a Count Down time contrast and display brightness and in the Configuration Mode IMPORTANT CODES 1200 The VFR code for any altitude in the US Refer to ICAO standards elsewhere 7000 The VFR code commonly used in Europe Refer to ICAO standards 7500 Hijack code Aircraft is subject to unlawful interference 7600 Loss of communications 7700 Emergency 7777 Military interceptor operations Never squawk this code 0000 Military use Not enterable 915 4 Page Date 19 February 2014 Pilot s Operating Handbook US Section 915 EXTRA 330LX GARMIN GTX 330 Transponder Avoid selecting code 7500 andall 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 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 ID
164. 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 correct 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 68 KIAS 120 126 km h A light pressure on the stick lifts the tail to horizontal position Rotate the aircraft at 68 KIAS 126 km h On reaching climb speed of 110 KIAS 204 km h proceed with climb Page Date 19 February 2014 4 7 Pilot s Operating Handbook US EXTRA 330LX X TRA 4 6 CLIMB Climbs may be performed up to maximum continuous RPM RPM above 2400 should however be used only when necessary for maximum performance in order to avoid unnecessary noise Turn boost pump OFF 4 7 CRUISE 1 Altitude As selected 2 Throttle RPM ADJUST for cruising speed 3 Mixture ADJUST for minimum fuel consumption 4 Trim 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 8 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 amp CENTER TANK position 4 8 2 APP
165. im servo located in the right rear fuselage It is controlled by a trim switch integrated in the control stick handle or in the instrument panel Trim position is indicated by a LED indicator on the instrument panel 7 6 INSTRUMENTATION The Extra 330LX 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 19 February 2014 7 5 7 Neu Pilot s Operating Handbook US Description and Operation of Aircraft and Systems X TRA EXTRA 330LX 7 6 1 INSTRUMENT PANEL REAR COCKPIT 999909999 20 16 Control Stick VY UU WV Er E 40 la 10 5 110 5 110 5 5 5 BOOST STROBE NAV a 7 8 9 10 11 12 13 14 15 16 17 18 Figure 2 Switches Circuit Breaker 7 6 Page Date 19 February 2014 Pilot s Operating Handbook US Section 7 EXTRA 330LX X TRA Description and Operation of Aircraft and Systems Position ltem Fig 1 COM G meter Volt Amperemeter Airspeed indicator Magn direction indicator Altimeter Manifold pressure fuel flow RPM Indicator Trim position indicator Transponder Magneto selector switch and starter Oil pressure oil temperature EGT CHT Fuel quantity c
166. in with the GTX 330 pilot s guide PN 190 00207 00 applicable revision you received with yourtransponder Page Date 19 February 2014 915 3 Section 915 Pilot s Operating Handbook US GARMIN GTX 330 Transponder EXTRA 330LX 915 1 1 MODE SELECTION KEYS OFF Powers off the GTX 330 STBY Selects the standby mode displaying the last active identification code When in standby mode the transponder will not reply to any interrogations ON Selects Mode A At power on the last active identification code will be selected In this mode the transponder replies to interrogations as indicated by the Reply Symbol Replies do not include altitude information ALT Powers on the transponder in Mode A and Mode C At power on the last active identification code will be selected In ALT mode the transponder replies to identification and altitude interrogations as indicated by the Reply Symbol Replies to altitude interrogations include standard pressure altitude received from a separate encoder 915 1 2 CODE SELECTION Code selection is done with eight keys 0 7 that provide 4 096 active identification codes Pushing one of these keys begins the code selection sequence The new code will not be activated until the fourth digit is entered Pressing the CLR key will move the cursor back to the previous digit Pressing the CLR key when the cursor is on the first key of the code or pressing the CRSR key during code entry w
167. irworthiness directives and periodical inspections 8 3 PILOT CONDUCTED PREVENTIVE MAINTENANCE Pilots operating the airplane should refer to the regulations of the country of certification for information of preventive maintenance that may be performed by pilots All other maintenance required on the airplane is to be accomplished by appropriately licensed personnel Airplane dealer should be contacted for further information Preventive maintenance should be accomplished with the appropriate service manual 8 4 ALTERATIONS OR REPAIR Alterations or repairs of the airplane must be accomplished by licensed personel Page Date 19 February 2014 8 3 Section 8 Pilot s Operating Handbook US Handling Servicing and Maintenance EXTRA 330LX 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 ring plates are provided at the wing tips The tail wheel leg can be used as third point to tie down the airplane If the aircraft is parked in the open it must be protected against the effects of weather the degree of protection depending on severity of the weather conditions and the expected duration of t
168. is can be achieved by using the same canopy frame hinges and latches included The front seat is covered by the flat portion of the frame in front of the canopy Operation of the locking mechanism is feasible only from the rear seat HANDLING SERVICE AND MAINTENANCE Not affected Page Date 19 February 2014 908 3 Section 908 Pilot s Operating Handbook US Single Seat Canopy XTRA EXTRA 330LX Left blank intentionally 908 4 Page Date 19 February 2014 Pilot s Operating Handbook US XTR A EXTRA 330LX SECTION 909 ARTEX ME 406 ELT Table of Contents Paragraph Page 909 1 GENERA m 909 3 909 2 NIFI cme 909 3 909 3 EMERGENCY PROCEDURES 225 anna na acu nu iun on nana na a RE EX n RE anna in da ERN ERR 909 4 909 4 NORMAL PROCEDURES 5 5 5 4 433163 nana a sinn ECCE Cu aaa e c a DE San nca SCR n Ea n 909 4 909 5 aiimeljhele c 909 4 909 6 WEIGHT amp CENTER OF GRAVITY 2 1 1 1 1141 1 909 4 909 7 SYSTEM DESGRIP TION o pou again aa rn rr Cn pua ud cn ra ea d ci dt d dec a Gn i 909 5 909 7 1 Seng re E 909 5 909 7 2 Test MO GG irte vetro tren eror hber aser bere Pert
169. is used as 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 19 February 2014 Pilot s Operating Handbook US Section 922 EXTRA 330LX XTR A 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 intercom Setup Source Monitoring NAV XPDR IDENT 117 95 7 1200 Pst 67 136 97 1 sare Audio Panel Mo
170. it 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 19 February 2014 Pilot s Operating Handbook US Section 922 EXTRA 330LX XTRA GARMIN GTN 635 650 750 To acknowledge or advance to the next page touc
171. itch has the 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 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 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 E
172. ke Syster ai ccicsies e 8 p Single Seat 4 Pigisq zz D 8 NAT AA83 001 8 BECKER 4401 Transponder 8 BECKER 6401 12 GARMIN GTX 327 Transponder 6 p GARMIN GTX 328 Transponder 8 p GARMIN GTX 330 Transponder i reote noeh 8 p GARMIN GNC 420W GNS 430W 8 p ASPENEFD1000 500 System eec cenc reser e centre nena namen nana usan 12 p e 0 p Landing EB e 4 p fnt FIOM diet 8 p reserved Mu M 0 p GARMINGTNO635 650 750 55 5 nn nnn 16 19 2014 9 Section 9 Z Pilot s Operating Handbook US Supplements XTRA EXTRA 330LX Left blank intentionally
173. lays the altitude data supplied to GTX 330 in feet hundreds of feet i e flight level or meters depending on configuration An arrow to the right of the altitude indicates that the airplane is climbing or descending Page Date 19 February 2014 915 5 Section 915 Pilot s Operating Handbook US GARMIN GTX 330 Transponder XTRA EXTRA 330LX FLIGHT TIME Displaysthe Flight Time controlled bythe START STOP and CLR keys when Automated Airborne Determination is configured as normal 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 The count up timer is controlled by the START STOP and CLR keys Pressing the CLR key zeros the display DOWN The count down timer is controlled by START STOP CLR and CRSR keys initial Count Down timeis entered with the 0 9 keys Pressing the CLR key resets thetimer to the initial value STBY The transponder will not reply to any interrogations GND This page is not active CONTRAST This page is only displayed if manual contrast mode is selected in Configuration Mode Contrast is controlled by the 8 and 9 keys DISPLAY This page is only displayed if manual backlighting mode is selected on Configuration Mode Backlighting is controlled by the 8 and 9 keys 915 1 5 CONFIGURATION MODE
174. light 911 4 Squawk selectiOli 911 5 Flight operation in Mode A transponder reply code 911 7 Flight operation in Mode reply code and altitude code 911 7 e ra 911 7 MOST 911 7 Configuration Mode 2 3 cinere tee t d Pe e pude 911 8 LIMITATIONS et cca es coe wees ase a ccc eee cesta secede eee 911 8 EMERGENCY PROCEDURES 6 ence 911 8 Important CodeS zouen isein anaana ae Aae ET 911 8 NORMAL PROCEDURES 911 8 PERFORMANCE Sanaa aeaaaee e aaa a ae a aae a aaa E a AAA E SEa 911 8 Page Date 19 February 2014 911 1 911 Pilot s Operating Handbook US BECKER ATC 4401 Transponder EXTRA 330LX Left blank intentionally 911 2 Page Date 19 February 2014 Pilot s Operating Handbook US Section 911 EXTRA 330LX BECKER 4401 Transponder 911 1 GENERAL The Becker panel mounted 4401 Transponder is a radio transmitter and receiver that fulfills the role of the airborne beacon equipment according to the requirements of the Air Traffic Radar Beacon System ATCRBS Its functionality includes replying to ATCRBS Mode A and Mode C interro
175. lights at day are allowed The be operated at OAT from 20 C 4 F to 44 111 Below temperatures of 10 C 14 F the oil vent line must be modified by the low temperature kit breather line Flight in known icing conditions is prohibited Smoking is prohibited 2 11 1 STRUCTURALTEMPERATURE COLOUR LIMITATION Structure is qualified up to 72 C 161 6 Structure temperatures composite above 72 161 6 F are not permitted Not to exceed this temperature limit color specification for composite structure has to be complied with To check the temperature inside the cockpit potential green house effect a reversible temperature indicator STRUCTURAL OVERHEAT INDICATOR is applied on the upper side of the wing main spar in the carry through section After reaching the temperature limit of 72 161 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 TIRE PRESSURE The tire pressure is 3 4 bar 49 psi 2 14 MARKINGS AND PLACARDS 2 14 4 AIRCRAFT IDENTIFICATION PLATE o TC NUMBER A67EU o FLUGZEUGPRODUKTIONS UND VERTRIEBS GMBH MODEL EA 300 LC oSERIAL NUMBER 2 8 Page Date 19 February 2014 Pilot s Operating Handbook US Section 2 EXTRA 330LX
176. lizer 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 Right Wing 1 Aileron freedom of movement and security CHECK 2 Trailingedge CHECK 3 Fueltank vent opening right landing gear CHECK 4 Fuel quantity CHECK 5 Fuel tank filler cap CHECK 4 4 Page Date 19 February 2014 Plots Operating Handbook US XIRA Section 4 Normal Procedures 6 Wing fuel tank drain 7 Rightlanding gear wheel 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 Pitot cover Trailing edge Aileron freedom of movement and security NO Oi 6 Before starting engine Preflightinspection Passenger briefing Parachute handling briefing Seats seatbelts shoulder harnesses Canopy Brake Battery switch Avionics power switch Electrical equipment Alternator Wingtip position Strobe lights DRAIN FORAT LEAST 4 SECONDS TO CLEAR SUMP OF POSSIBLE WATER CHECK CLOSED CHECK CHECK CHECK CHECK DRAIN FORAT LEAST 4 SECONDS TO CLEAR SUMP OF POSSIBLE WATER CHECK CLOSED DRAIN FORAT LEAST 4SECONDS TOCLEAR FI
177. lly 915 8 Page Date 19 February 2014 Pilot s Operating Handbook US XTRA EXTRA 330LX 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 PON 916 3 B arigen m c 916 3 PIACANOS D 916 4 EMERGENCY ABNORMAL PROCEDURES 916 4 Emergency Procedures tei cento tme ace 916 4 Abnormal Procedur S th net RAN ERR sud 916 4 lt 916 5 PERFORMANCE Ke 916 5 WEIGHT amp CENTER OF GRAVITY retten nnd aee taie 916 5 SYSTEM DESCRIPTION 222i e aeneo canem sete eo 916 5 Key and Knob 916 5 WIENER 916 7 Page Date 19 February 2014 916 1 Section 916 Z Pilot s Operating Handbook US GARMIN GNC 420W GNS 430W EXTRA 330LX Left blank intentionally 916 2 Page Date 19 February 2014 Pilot s Operating Hand
178. lot isolation fail safe direct connection to the aircraft radio system are standard features 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 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 19 February 2014 910 3 Section 910 Pilot s Operating Handbook US NAT AA83 001 Intercom EXTRA 330LX 9103 EMERGENCY PROCEDURES Not applicable 910 4 NORMAL PROCEDURES Not applicable 9105 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 cs yg Dual Control ee ICS Volume inner LIVE lt lt MAX Pilot VOX outer
179. lume 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 NAVCOM pages will be the primary pages used for navigation The default NA Vpagedisplays a graphic course deviation indicator CDI the active leg of your flight plan as defined by the current and to waypoints and six user selectable data fields The default settings for these fields are distance to waypoint DIS desired track DTK bearing to waypoint BRG ground speed GS ground track TRK and estimated time en route ETE The default NAV page is selected by pressing and holding the CLR key orturning the small right knob Page Date 19 February 2014 916 7 Section 916 Z Pilot s Operating Handbook US GARMIN GNC 420W GNS 430W EXTRA 330LX Left blank intentionally 916 8 Page Date 19 February 2014 Pilot s Operating Handbook US XTRA EXTRA 330LX Paragraph 917 1 917 1 1 917 2 917 2 1
180. m h headwind the 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 OAT 0 C 32 F 15 59 F 30 C 86 F Rotate PA T O T O T O T O T O T O weight Speed Roll over Roll over Roll over 15 m 50 ft 15 m 50 ft 15 m 50 ft kg KIAS ft m m ft m ft m ft m ft m ft m ft lbs km h 950 68 SL 96 315 207 679 115 377 248 813 133 436 285 935 2095 126 2000 610 115 377 248 814 138 453 298 978 160 525 342 1122 4000 1219 138 453 298 978 166 545 357 1171 192 630 410 1345 6000 1829 166 545 358 1175 199 653 429 1407 230 755 492 1614 870 65 SL 78 256 167 548 93 305 200 656 107 351 230 755 1918 120 2000 610 94 308 200 656 112 367 240 787 128 420 276 906 4000 1219 112 367 241 791 134 440 288 945 154 505 331 1086 6000 1829 135 443 289 948 161 528 346 1135 185 607 397 1302 820 63 SL 67 220 114 374 79 259 170 558 93 305 200 656 1808 117 2000 610 80 262 173 568 95 312 204 669 112 367 240 787 4000 1219 97 318 207 679 114 374 248 814 134 440 288 945 6000 1829 116 381 249 817 137 449 294 965 161 528 347 1138 5 8 Page Date 19 February 2014 Section 5 Perform
181. 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 for testing of ELT s CAUTION Do not allow test duration to exceed 5 seconds A false alarm may be generated Any time the ELT is activated itis transmitting a 121 5 MHz distress signal After approximately 50 seconds a 406 MHz distress signal is transmitted and is considered valid by the satellite system Whenever the ELT is switched from ON to ARM a 406 MHz signal is transmitted however itis specially coded as a self test signal that is ignored by the COSPAS SARSAT satellites 909 8 2 SELFTEST Tune areceiver usually the aircraft radio to 121 5 MHz Turnthe ELT aircraft panel switch for about 1 second then back to the position The receiver should voice about audio sweeps e At turn off back to ARM state the panel LED should present 1 pulse buzzer will not sound for 1 pulse If more are displayed determine the problem from the list
182. n 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 Do not open engine compartment access doors while engine is on fire 3 6 Page Date 19 February 2014 Pilot s Operating Handbook US EXTRA 330LX XIRA Section 3 Emergency Procedures 3 4 2 IF ENGINE FAILS TO START 1 Cranking 2 Throttle 3 Mixture 4 Fuel shutoff valve If fire is extinguished 5 Battery switch 6 Alternator switch 7 Ignition switch 8 Engine compartment 3 4 3 ENGINE FIRE IN FLIGHT 1 Mixture 2 Fuelshutoff valve 3 Battery switch 4 Alternator switch 5 Airspeed 6 Land 3 5 ICING 3 5 1 INADVERTENT ICING ENCOUNTER CONTINUE FULL OPEN IDLE CUT OFF OFF Pull amp Turn OFF OFF OFF INSPECT IDLE CUT OFF OFF Pull amp Turn OFF OFF 100 KIAS 185 km h find your airspeed attitude which will keep the fire away from the cockpit AS SOON AS POSSIBLE 1 Turn back or change altitude to obtain an outside temperature that is less conductive to icing
183. nciations 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 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 19 February 2014 Pilot s Operating Handbook US Section 922 EXTRA 330LX 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 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 information 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
184. ne A 902 3 902 7 DESCRIPTION OF THE SYSTEM serene nnne nnne nnne nnns 902 4 902 8 HANDLING SERVICING AND MAINTENANCE nennen nennen nnne 902 4 Page Date 19 Februar 2014 902 1 Section 902 Pilot s Operating Handbook US Electric Pedal Adjustment XTRA EXTRA 330LX Left blank intentionally 902 2 Page Date 19 Februar 2014 Pilot s Operating Handbook US Section 902 EXTRA 330LX X TRA Electric Pedal Adjustment 902 902 1 902 2 902 3 902 4 902 5 902 6 ELECTRIC PEDAL ADJUSTMENT GENERAL improve seat and control convenience the EXTRA 330LX 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 an
185. ng 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 9034 NORMALPROCEDURES Not affected 903 5 PERFORMANCE Not affected 9036 WEIGHT amp CENTER OF GRAVITY Refer to the equipment list in Section 6 of this Handbook Page Date 19 February 2014 903 3 Section 903 XTR A Pilots Operating Handbook US Cabin Heating System EXTRA 330LX 903 7 SYSTEM DESCRIPTION Onthe 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 ofthe 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 wa
186. nitored Radios Selection Activates 1 1 Split Split Mod Mode ju Mon Selection 10r2 Recorder 2 2 Playback Playback Monitor and Control Contro s Passenger Mic Selections Address Cabin speaker Not used Speaker Marker Not used Audia Volume Marker Not used Hi Sense mE i Demo CPS TTP Tom Freq 775 Figure 5 GTN 750 Audio Panel Operation Page Date 19 February 2014 922 13 Section 922 Z Pilot s Operating Handbook US GARMIN GTN 635 650 750 XTRA EXTRA 330LX 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 un
187. nopy 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 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 19 February 2014 Pilot s Operating Handbook US 4 EXTRA 330LX XTRA Normal Procedures 4 5 TAKE OFF PROCEDURE 4 5 1 BEFORE TAKE 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 attation to the three small LEDs in the Status area on the upper left corner of the P 1000 face Ignition switch position LEFT Status area Right red LED illuminates Display shows RPM drop 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 is 175 The maximum difference between the magnetos shall not to be more than 50 RPM identify with the
188. nose up and establish a shallow descend by adjusting throttle To flare the plane gently increase power to bring the nose up to landing attitude 3 8 Page Date 19 February 2014 Pilot s Operating Handbook US XIRA EXTRA330LX SECTION 4 NORMAL PROCEDURES Table of Contents Paragraph Page 4 0 ic zd X 4 3 4 0 1 Airspeeds for Normal Operation 4 3 4 0 2 Checklist and Procedures tecta teta cuta antena acuta ne rana a Du n and 4 3 4 1 PREFEIGHT INSPECTION 4 4 4 2 CHECKLISTPROGEDUBRES 44 43 STARTING PROCEDURES nissin iaa eeaeee aaaea 46 4 3 1 4 6 4 3 2 UE 4 6 4 4 TAXIING THE AIRCRAFT lt lt lt lt lt 4 6 4 5 TAKE OFF PROCEDURE 4 7 4 5 1 ise Take Off EE 4 7 4 5 2 PT 4 7 4 6 eB 4 8 4 7 CRUISE 4 8 4 8 LANDING PROCEDURES reitera cuerno cce eres unadi rana mn aec Dora nane Iu Eso sr Ema n enr eia aDecn
189. ntercom 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 ISOLATION 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 us
190. oard of aviation in the country the aircraft is registered Page Date 19 February 2014 Pilot s Operating Handbook US XIRA WARNINGS CAUTIONS AND NOTES The following definitions apply to Warnings Cautions and Notes gt Operating procedures techniques etc which could result in personal injury loss of life if not carefully followed CAUTION gt Operating procedures techniques etc which could result in damage to equipment if not carefully followed NOTE 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 permissible Page Date 19 February 2014 MAIN TABLE 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 19 February 2014 Plots Opening Handbook US XIRA SECTION 1 GENERAL Table of Contents Paragraph Page 1 0 pixjeubae me 1 3 1 1 SPECIFICATION OF CLASS
191. ode 912 1 10 CONFIGURATION MODE The configuration mode is available from SBY mode only To get into configuration mode press button SEL G turn rotary encoder B until CFG appears in the bottom row of the display Refer to Pilot s Guide for available options 912 2 LIMITATIONS Notapplicable 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 19 February 2014 Pilot s Operating Handbook US XTRA EXTRA 330LX 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 GENERAL iissa M HQ 913 3 Mode Selection Keys tete ete etes nn HERR ean a 913 3 exu 913 4 Keys for other GTX327 FUNCUONS assent eee Deer Due et rene rk Ea Poco ume 913 4 LIMITATIONS E 913 6 EMERGENCY PROCEDURES 5 eoe td aede ua xl a ele ctia de dae 913 6 important CodeS c 913 6
192. one 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 Page Date 19 February 2014 910 5 Section 910 Pilot s Operating Handbook US NAT AA83 001 Intercom EXTRA 330LX 910 7 2 OPERATION VOX OPERATION The VOX control is used to set the level of audio required to activate the microphones AA83 001 provides three modes of intercom operation selected by the position of the VOX control LIVE ICS When the VOX control is positioned fully 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 i
193. or left magneto systems Between the left and right magneto ignition system alert indicators is a yellow rpm Synchronization indicator This small yellow indicator is illuminated when there is a difference of more than 50 rpm between the right and left tachometers This indicator also may flicker during extreme rpm excursions of the engine OPERATION BUTTONS There are three panel buttons Each button has two modes of operation PRESS AND HOLD operation mode press and hold for more than 2 3 of a second This operation mode is placarded above each button Hours Clear Trap Engine time Hours The left button upon depression will cause the tachometer to display the non fractional portion 0000 of the current accumulated engine hours When the button is released the fractional part of the engine hours 00 is displayed for a short period of time The clock is started whenever the engine rpm exceeds 800 rpm and is recorded in real hours Clear Clear The middle button clears the rpm trap During depression of the switch the rpm trap is zeroed When the button is released the trap will record the current 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 Page Date 19 February 2014 906 5 Section 906 m Pilot s Operating Handbook US Digital RPM Indicator XTRA EXTRA
194. play 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 ofthe indicator Ignition Switch Tachometer Magneto Alert Indicator Lights Position LEFT Status LED RIGHT Status LED OFF ON ON RIGHT ON OFF LEFT OFF ON BOTH OFF OFF 906 4 Page Date 19 February 2014 Pilot s Operating Handbook US Section 906 EXTRA 330LX XTRA Digital RPM Indicator RPM RANGES The face of the indicator is placarded with the respective engine rpm operating range Additionally the engine operating ranges are indicated by the large green yellow and red LEDs These LEDs are located on the upper right corner of the indicator face Green Yellow Bede 700 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
195. previous digit Pressing the CLR key when the cursor is on the first key of the code or pressing the CRSR key during code entry will remove the cursor and cancel data entry restoring the previous code The numbers 8 and 9 are not used for code entry only for entering a Count Down time and in Configuration Mode IMPORTANT CODES 1200 The VFR code for any altitude in the US Refer to ICAO standards elsewhere 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 KEYS FOR OTHER GTX327 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 918 4 Page Date 19 February 2014 Pilot s Operating Handbook US Section 913 EXTRA 330LX GARMIN
196. rm 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 d 3 E d 4 NY Firewall 5 AL NL 6 r T fwd A 7 SCA a l Figure 1 903 8 HANDLING SERVICING AND MAINTENANCE Not affected 903 4 Page Date 19 February 2014 Operating Handbook US XIRA SECTION 904 ACCELEROMETER TL 3424 EXT Table of Contents Paragraph Page 904 1 GENERALE nea eaedem iamen uic BEER 904 3 904 2 LIMITATIONS occian 904 3 904 3 EMERGENCY PROCEDURES 5 rre aana AE a 904 3 904 4 NORMAL PROCEDURES 904 3 904 5 PERFORMANGE 904 3 904 6 WEIGHT AND BALANCE rente cox e eeu Gu Oc ra ne Enna cv 904 4 904 7 iajzeliis R 904 4 Page Date 19 February 2014 904 1 Section 904 Pilot s Operating Handbook US Accelerometer TL 3424 EXT X TRA EXTRA 330LX Left blank intentionally 904 2 Page Date 19 February 2014 Pilot s Operating Handbook US Section 904 EXTRA 330LX X TRA Accelerometer TL 3424_EXT 904 904 1 904 2 904 3 904 4 904 5 ACCELEROMETER TL
197. rtant CodeS tet asas RERO 912 10 lt lt 912 10 sisi el 912 10 Page Date 19 February 2014 912 1 Section 912 Pilot s Operating Handbook US BECKER 6401 Transponder EXTRA 330LX Left blank intentionally 912 2 Page Date 19 February 2014 Pilot s Operating Handbook US Section 912 EXTRA 330LX BECKER BXP 6401 Transponder 912 1 GENERAL The Becker panel mounted 6401 Transponder is a radio transmitter and receiver that fulfills the role of the airborne beacon equipment according to the requirements of the Air Traffic Radar Beacon System ATCRBS Its functionality includes replying to ATCRBS Mode A C and Mode S interrogations Itoperates on radar frequencies receiving ground radar interrogations at 1030 MHz andtransmitting acoded 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 19 Feb
198. ruary 2014 912 3 912 BECKER 6401 Transponder Pilot s Operating Handbook US EXTRA 330LX 912 1 1 CONTROLS ANDINDICATORS A Mode Selector Rotary switch with 4 positions OFF position Transponder is switched off 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 mode of C Rotary switch to change settings 16 steps per turn C Button Push button Push to jump from digit to digit for settings or from mode of B one menu to the next generally used as an enter key D Push button Activates the Special Identifier SPI in ad dition to the reply code for approx 18 seconds during this time ID appears in the LC display E Display part 1 2 line LCD display Displays the following informations code indication in the top row flight level in the bottom row various informations in the bottom row additional indicators on the left side see Ref H F STO Push button Stores the selected values to the settings G SEL Push button Opens and selects the menu Display part 2 LCD indicators Displays additional indicators R for reply ID for dent ALT for XPDR ALT mode or ON for XPDR ON mode FL for flig
199. speeds above 140 KIAS 259 km h Segment 1 4 loop climbing The minimum recommended speed is 100 KIAS 185 km h If the maneuver is to be followed by a vertical line a higher entry speed is required depending on the expected length of the line A complete loop can be performed at speeds above 100 KIAS 185 km h NOTE Since the maximum horizontal speed is 185 KIAS 343 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 If performing gyroscopic maneuver such as flat spin power or knife edge spin reduce RPM to 2400 in order to minimize the gyroscopic forces Page Date 19 February 2014 4 11 Section 4 Pilot s Operating Handbook US Normal Procedures EXTRA 330LX 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
200. sponder 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 setin 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 onthe radar screen ofthe controller Idt appears in the bottom line ofthe 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 ThelBIT Initiated Built in Test can be activated in any mode excluding the configuration mode with the push of F and atthe same time The action starts with the leading edge ofthe second pushed button The IBIT works as follows in all modes The test starts with all available test routines including the transmitter test routine During the test is indicated on the display The testtakes notlongerthan 1 second Ifthe IBIT was succ
201. 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 Page Date 19 February 2014 917 3 Section 917 Pilot s Operating Handbook US ASPEN EFD1000 500 System XTRA EXTRA 330LX This supplementis written for MAP SOFTWARE RELEASE 2 4 1 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 9172 LIMITATIONS This supplement does not grant approval for IFR operations The Aspen flight displays have been installed on a no hazard no credit basis Th
202. t appears The intended function of the Flight Path Marker is to display the current vertical and lateral path of the aircraftbased ontwo 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 information during turns transitions to climb or descent or acrobatics Theintendedfunction ofthe 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 19 February 2014 917 11 Section 917 Pilot s Operating Handbook US ASPEN EFD1000 500 System XTRA EXTRA 330LX if the aircraft continues the collision path In addition the terrain is colored based on the aircraft proximity to the terrain yellow when the aircraft is within 500 feetvertically ofthe 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
203. tem TWS uses the 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 responsible 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 but no 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 mostlike the outside view in the narrow FOV1 view and a more expansive view ofthe horizonis available in FOV2 The terrain depicted in FOV2 is closer than i
204. tered If a Company Call Sign is mentioned this has to be entered To enter it see below It willbe stored inthe EEPROM ofthe control head In this case the indication on the display changes to Flight Number If the Call Sign Tail Number is mentioned no change as it is the default setting from the Address Module Page Date 19 February 2014 912 7 912 2 Pilot s Operating Handbook US BECKER BXP 6401 Transponder EXTRA 330LX SETTING THEFLIGHTNUMBER 1 2 Press SEL button G to enter the select mode Rotate B until is displayed Push C to switch to FN The cursor is set on the first character Rotate B to change this character Push C to set the cursor to the next character Repeat steps 4 and 5 until the flight number is entered If the flight number consists of less than 7 characters put a space at the end to fill the remaining characters with spaces Storethe changes with STO button F Forleavingthe 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 AI Press SEL button G to enter the select mode Rotate B to the indication FN XXXXXXXxX First push on
205. tertheswitch ontesthas elapsed and no error message is written in the display the transponder switches to the mode set on the mode switch A NOTE The blind encoder is only powered if the transponder is not switched OFF at least SBY A blind encoder needs a warm up time sometimes a several minutes Therefore although the solid state transponder needs no warm up time turn the transponder to SBY immediately after starting the engine 911 1 3 SQUAWKSELECTION 1 The transponder remains switched in the standby mode until requested by the ground station to transmit a code e g Squawk alpha 6426 Using the double rotary switch B C set the 4 digit code requested by ATC as follows Using switch B move the cursor to the particular digit Digits 0 to 7 can then be set using switch If switch isturned clockwise or counter clockwise the cursor is moved one position to the right or the left The cursor appears only in the code display and is indicated by the flashing digit If no cursor is visible the first digit flashes after a clockwise rotation and the last digit after a counter clockwise rotation When the code is being changed in the ON or ALT position the transponder temporarily switches to the standby mode The active time of the cursor and the rate of flashing can be changed in the configuration mode If the cursor is not moved again within of 3 seconds can be changed in configuration mo
206. 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 19 February 2014 Pilot s Operating Handbook US Section 916 EXTRA 330LX XTRA GARMIN GNC 420W GNS 430W The flight plan key FPL allows you to create edit activate and invert flight plans as well 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 you to select and remove approaches departures and arrivals from your flight plan When using a flight 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 left corner of the unit Turning it clockwise will turn unit power on and increase the COM radio vo
207. 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 aircrafts 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 330 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 PN CAUTION The GTX 330 should be turned off before starting or shutting down aircraft engine TheGTX330 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 Thissupplementis 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 here
208. tion 902 8 HANDLING SERVICING AND MAINTENANCE Not affected 902 4 Page Date 19 Februar 2014 Pilot s Operating Handbook US XTR A EXTRA 330LX SECTION 903 CABIN HEATING SYSTEM Table of Contents Paragraph Page 903 1 GENERAL 903 3 903 2 B rylecm 9 903 3 903 3 5 22222400044 ETTE nnnc uS 903 3 903 4 NORMAL PROCEDURES veas annee ck Y ka 903 3 903 5 PERFORMANCE ocsi ule du dor HAE 903 3 903 6 WEIGHT 903 3 903 7 SYSTEM DESCRIPTION 903 4 903 8 HANDLING SERVICING AND MAINTENANCE 903 4 Page Date 19 February 2014 903 1 Section 903 XTRA Pilots Operating Handbook US Cabin Heating System EXTRA 330LX Left blank intentionally 903 2 Page Date 19 February 2014 Pilot s Operating Handbook US XTRA Section 903 EXTRA 330LX Cabin Heating System 903 1 GENERAL The 330LX can be equipped with a cabin heati
209. tion 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 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 including the 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 post
210. transmitting 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 pulse for 18 seconds Mode S transmit receive capability also requires 1090 MHz transmitting and1030 MHz receiving for Mode S functions In addition to displaying the code reply symbol and mode of operation the GTX 328 screen will display pressure altitude and timer functions The displayed pressure altitude may not agree with the aircrafts 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 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
211. tures 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 sequencing of waypoints Whenever OBS mode is selected you may set the desired course to from a waypoint using
212. u 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 19 February 2014 922 11 Section 922 Z Pilot s Operating Handbook US GARMIN GTN 635 650 750 XTRA EXTRA 330LX 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 special indicators in automated facilities Only the code 7500 will be decoded as the hijack code An aircraft s transponder code if available is utilized to enhance the tracking capabilities of the ATC facility therefore care should be taken when making routine code changes NOTE When an Aspen EFD1000 15 installed it
213. ular 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 105 except otherwise stated 2 Take off andlanding on concrete surface 3 Nowind 4 Standard atmospheric condition 5 1 2 Definitions of Terms For definition of terms abbreviations and symbols refer to section 1 General 5 1 3 Sample Problem TAKE OFF CONDITIONS Field Pressure Alt 2000 ft 610 m Temperature 15 C 59 F Wind Component Headwind 8KT 15 km h Field Length 3000 ft 914 m CRUISE CONDITIONS Total Distance 400 NM 741 km Pressure Altitude 8000 ft 2438 m Temperature ISA 1 C 30 F Page Date 19 February 2014 5 3 5 Pilot s Operating Handbook US Performance EXTRA 330LX TAKE OFF Take Off Distance is shown by Fig 5 5 Example T O Weight 870 kg 1918 105 Ground Roll 112 m 367 ft Total Distance to clear a 50 ft obstacle 248 m 813 ft These distances are well within the available field length incl the 8 kts 15 km h headwind RATEOF CLIMB Fig 5 6 shows the Rate Of Climb using Take off Power The
214. 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 ABNORMALPROCEDURES GPS NAVIGATION INFORMATION NOT AVAILABLE OR INVALID If GTN635 650 750 GPS navigation information is not available or invalid 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 of flight or periodically cross check the GPS guidance toother approved means of navigation 922 6 Page Date 19 February 2014 Pilot s Operating Handbook US Section 922 EXTRA 330LX XTRA GARMIN GTN 635 650 750 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 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
215. uration 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 lt 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 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 19 February 2014 Pilot s Operating Handbook US Section 911 XTRA BECKER 4401 Transponder EXTRA 330LX 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 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 t
216. utton F was not used no change has been stored 912 1 8 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 19 February 2014 912 9 Section 912 Pilot s Operating Handbook US BECKER BXP 6401 Transponder EXTRA 330LX 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 c
217. w Annunciations Hints Xpdr Panel Controls Figure 1 GTN 6xx Display Layout 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 19 February 2014 922 3 Section 922 Z Pilot s Operating Handbook US GARMIN GTN 635 650 750 XTRA EXTRA 330LX Active Com Channel Standby Nav Standby Com Active Nav Channel Channel Channel Volume Squelch 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 Annu
218. 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 Depending on the alternator installed the maximum alternator output varies from 55 to 65 A Refer to the Equipment List in Section 6 for identification of alternator installed 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 manufactured 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 19 February 2014
219. 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 functional 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 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
220. y 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 19 February 2014 Opening Handbook US XIRA SECTION 906 DIGITAL RPM INDICATOR Table of Contents Paragraph Page 906 1 GENERAL 906 3 906 2 M rye cme 906 3 906 3 EMERGENCY PROCEDURES 1 5 aac n nurus 906 3 906 4 NORMAL PROCEDURES 906 3 906 5 dde i sc 906 3 906 6 WEIGHT AND AE 906 4 906 7 DESCRIPTION AND OPERATION OF THE SYSTEM 906 4 906 8 HANDLING SERVICING AND MAINTENANCE 906 6 Page Date 19 February 2014 906 1 Section 906 Pilot s Operating Handbook US Digital RPM Indicator XTRA EXTRA 330LX Left blank intentionally 906 2 Page Date 19 February 2014 Pilot s Operating Handbook US Section 906 EXTRA 330LX XTRA Digital RPM Indicator 906 906 1 906 2 906 3 906 4 906 5 DIGITAL
221. y storing the last recorded 30 minutes 20 000 lines entries every 0 1 seconds 2 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 The following values or definitions are preset in the configuration ofthe TL 3424 EXT WARNING MAX WARNING MIN ALARM MAX ALARMMIN SPEEDLIMIT Record begins at LANGUAGE SAMPLE RATE 49 5 9 9 5g 10 19 10 19 220 KIAS 50 KIAS English 0 1 Page Date 19 February 2014 904 5 Section 904 Pilot s Operating Handbook US Accelerometer TL 3424 EXT X TRA EXTRA 330LX SYMBOLS Thefollowing symbols are used inthe TL 3424 EXT display Display Symbol Meaning gt recording to memory 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 d
222. 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 19 February 2014 916 3 Section 916 Pilot s Operating Handbook US GARMIN GNC 420W GNS 430W XTRA EXTRA 330LX 916 2 1 PLACARDS GARMIN GPS limited to VFR use only In the clear view of the pilot Next to the 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 acrobatics the GPS signal can get lost 1 Reset switch OFF and ON the unit to regain the GPS signal SEARCHING A NEARBY AIRPOR

U.S. Version [Last Updated on: Jun 13th, 2014]

Contents

Download Pdf Manuals

Related Search

Related Contents