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Airplane Flight Manual XA42

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1. 1 08 81 INTRODUCTION uuu aaa a a nein 1 08 8 2 AIRPLANE INSPECTION PERIODS aa Rn nn RER RER nun nn nn nn nn ann anne nen 1 08 8 3 PILOT CONDUCTED PREVENTIVE MAINTENANCE a nennen nennen nen 1 08 8 4 ALTERATIONS OR REPAIR nuesnsnsnsnsnennnnnnnnnn non nnnn ern nenn nun nn nnn nun anne nen nnnn nennen nun ernennen 1 08 85 SERVICING is unir 1 08 8 6 GOUND HANDLING u u ponani nenn nirani anaa anpa aA ei nen nnnn nen inpar in 2 08 8 7 CLEANING AND PROTECTION coooconcccncccncccncocononcnoncocnnonnronononnnrnaronarennrenneraronarenonananon 2 08 Page date Page V 24 01 2011 PT A Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 INTRODUCTION This Airplane Flight Manual contains 9 chapters and includes the material required to be known by the pilot according to EASA CS 23 It also contains supplementary data supplied by XtremeAir GmbH NOTES This Airplane Flight Manual applies only to the aircraft whose nationality and registration marks are noted on the title page This Airplane Flight Manual is only valid in connection with the latest approved revision It is the responsibility of the pilot to be familiar with the contents of this Airplane Flight Manual including revisions and any relevant supplements Pages of this Airplane Flight Manual must not be exchanged and no alterations of or additions to the approved contents may be made with
2. cccccsecceeceeseeeseeeceeeceescueecueeueeanenaeenaeseeeseesnaueseueseneags 2 04 4 4 STARTING PROCEDURES u u uuu uu u u uu Susa saya reno ANENE Eana 5 04 4 5 TAXING THE AIRCRAFT a aaa nn anne 5 04 46 TAKE OFF PROCEDURES uu u u u uu aaa 6 04 4 7 COMBiininain adria 7 04 4 8 CRUISE iia cris 7 04 4 9 LANDING PROCEDURES concisa naaa aid 7 04 4 10 SHUTDOWN 2 uuu ul id mapa 8 04 4 11 AFTER LEAVING THE AIRCRAFT ccccsccseccceesceecesceeecueecuseuseasenasenaesnaeseseseseaneseneeas 9 04 4 12 ACROBATIC MANEUVERS 0occcocononcnnccnnccnnonoronoronaronconnroonrnnnnrnnnrna neon rennrrnrera reno nenarenanon 9 04 5 PERFORMANCE cccococcornccn nu nun nun nn nun nn nun nn nn nun nn nun nun un ne nun nununnunnun nenn 1 05 51 GENERAL ius aha iii 1 05 5 2 ISA CONVERSION cisco a nn 2 05 5 3 AIRSPEED CALIBRATION u cu ira 3 05 54 STAL SPEED cuidada ernennen enter 3 05 5 5 TAKE OFF PERFORMANCE nnnzensnennnnnnnnnnnnnnnnnnonnn nun nennen nun nennen nennen nennen nenn ennnan nn 4 05 5 6 RATE OF CLIMB PERFORMANCE zueensessnnnnnnnnnnnnnnnnnnnnn nen nnnnnnnn nennen nen nun nun nennen nn 6 05 5 7 CRUISE PERFORMANCE RANGE ENDURANCE AND FUEL CONSUMTION 6 05 5 8 LANDING PERFORMANCE o ccocccocccoconcnoncccnnoconoconconnrnnnonaronnronrrrnronnrenarencrrnrronnennnnonncnnnes 7 05 6 WEIGHT amp BALANCE iii 1 06 6 1 GENERA Liu ld 1 06 6 2 AIRCRAFT WEIGHING PROCEDURE cssccsseceseeeseeeeeneeseseeeeeseeeseeeseee
3. 1 15 R A ee EN ne ren 7 m R 1 Fuel Pressure Indicator UMA T04 212U 100 010 0 16 1 15 R 1 Fuel Pressure Sensor UMA T1EU 100G 0 09 0 18 R 1 Manifold Pressure UMA 7 100 20 0 14 1 15 R 1 EGT CHT Indicator JPI EDM 100 6C 0 15 1 19 R 1 Radio Funkwerk Avionics ATR 500 0 40 1 20 R 1 Radio Antenna Comant CI 122 0 39 2 33 R 1 Transponder Funkwerk Avionics TRT 800H 0 60 1 20 O 1 Transponder Antenna Comant CI 105 0 10 0 36 O 1 ELT Kannad 406 AF Compact 0 85 2 40 O 1 ELT Antenna RAMI AV 200 0 18 2 90 O 2 Brake Master Cylinder Beringer HBA01 0 10 0 80 R 2 Brake Fluid Reservoir Beringer Reservoir Kit 0 02 0 80 R 1 Safety Belt Assy Hooker Harness 1H 2130 J 4 00 1 69 R 1 Smoke Oil Pump Marco 164 020 12 1 40 2 40 O 1 Sighting Device LH XtremeAir GmbH XA42 5770 101 0 10 1 42 O 1 Sighting Device RH XtremeAir GmbH XA42 5770 102 0 10 1 42 0 Page 6 Page date Chapter 06 EASA approved 24 01 2011 PT A Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 Intentionally left blank Page date Page 7 24 01 2011 EASA approved Chapter 06 Airplane Flight Manual XA42 png A AFM XA42 0040 002 A 01 7 DESCRIPTION AND OPERATION OF AIRCRAFT AND SYSTEMS 7 1 AIRCRAFT The XA42 is designed and manufactured by XtremeAir GmbH Harzstra e 2 Am Flughafen Cochstedt 39444 Hecklingen Germany in accordance with the EASA CS 23 categories utility and acrobatic to fulfill normal operations and acrobatic flying up to the Unlimited aerobatic level
4. 24 01 2011 ramas 4 6 TAKEOFF PROCEDURES 4 6 1 BEFORE TAKEOFF Run up Canopy closed and locked Straps Fuel selector to fuselage tank Fuel capacity Electric fuel pump Engine instrument readouts in the GREEN Mixture Brakes Elevator pulled Propeller control Throttle to 1700 rpm Magnetos 1 2 Max RPM drop 175 rpm Max RPM difference 50 rpm Propeller control Afterwards Throttle to Idle RPM 700 rpm Controls free 4 6 2 TAKEOFF Normal takeoff Throttle 30 kts lift tail wheel O 75 kts 90 kts Takeoff in crosswind Throttle RPM Acrobatic RPM max 2700 rpm RPM Utility RPM max 2670 rpm Elevator 70 kts in three point attitude Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 CHECK TIGHTEN CHECK CHECK ON CHECK PUSH FULL RICH APPLY KEEP PUSH FINE PITCH ADJUST CHECK CHECK CHECK 3 x PULL COARSE PITCH PUSH FINE PITCH ADJUST CHECK FULL OPEN PUSH LIFTOFF CLIMB FULL OPEN ADJUST ADJUST NEUTRAL LIFTOFF No turns below 90 kts 90 kts Page date 24 01 2011 CLIMB Page 6 Chapter 04 Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 4 7 CLIMB Takeoff power Acrobatic RPM max 2700 rpm Utility RPM max 2670 rpm Manifold pressure Airspeeds Normal climb Best rate of climb Best angle of climb 4 8 CRUISE Max continuous power RPM max 2500 rpm Manifold pressure Set Mixture according to EGT Indicator Select right left
5. The aircraft is a two seat light weight single engine construction with a carbon fiber reinforced composite fuselage structure The primary structure is carbon fiber reinforced composite The items are qualified up to 85 C 185 F To avoid high temperatures the painting has to meet the requirements under color specification for composite structure The standard aircraft is designed to operate within a range of ambient air temperature from 20 C to 38 C 4 F to 100 F at sea level It is possible to start the engine using the aircraft battery at 20 C 4 F without preheating 7 2 FUSELAGE The fuselage is made out of carbon honeycomb sandwich Canopy frame and the empennage are part of the fuselage structure The fuselage also includes the substructure of the seats and the instrument panels The canopy itself is a single carbon fiber reinforced composite part It opens to the right hand side is locked on the left hand side and its opening angle is limited by a strap Emergency jettison is achieved by simply unlocking the canopy while the lower pressure on the upper outside of the canopy will pull it up and tear it away 7 3 WING The wing shell is designed as CFRP sandwich shell which is closed by an aft shear web An overlap joint laminated with the lower wing shell provides bonding of the two wing shells at the wing nose area The wing spar is designed as double box type spar and guided through the fuselage as on
6. km h Ibs MP NM rpm CG Arm Moment SL Page date 24 01 2011 Feet per minute Feet 1 ft 304 8 mm Inch 1 in 25 4 mm Meter Liter US liquid gallon 1 US gal 3 79 Liter US liquid quart 1 US qt 0 946 Liter Horse power English Hour Knots nautical miles per hour Kilometer per hour English pound 1 Ibs 0 4536 kg Manifold pressure Nautical mile 1 nm 1 852 km Revolutions per minute Center of gravity Is the horizontal distance from reference datum Is the product of the weight of an item multiplied by its arm Sea level Page 6 Chapter 01 Airplane Flight Manual XA42 png A AFM XA42 0040 002 A 01 1 13 CONERVERSION TABLE Page 7 Page date Chapter 01 24 01 2011 PT A Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 Intentionally left blank Page date Page 8 24 01 2011 Chapter 01 Airplane Flight Manual XA42 png A AFM XA42 0040 002 A 01 2 LIMITATIONS 2 1 GENERAL This chapter includes limitations for operation of the aircraft the engine the standard systems and the standard equipment Also it gives information on the instrument markings and basic placards The limitations in this chapter have been approved by the EASA Observance of these operating limitations is required by national aviation regulations In case of an XA42 is equipped with specific options additional information required for safe operation will be contained in chapter 9 Instrum
7. 174 322 225 417 z Reduce 45 diving Vs 225 417 NL Ken Ls i Reduce 90 diving Vs 225 417 throttle Looping 100 185 225 417 Stall turn 100 185 225 417 Page 4 Page date Chapter 02 24 01 2011 Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 MS Recommended entry speeds IAS Maneuvers Symbol Remarks Min kts km h Max kts km h Snap roll 80 148 174 322 E GE Tail slide 100 185 225 417 I Spin Vs gt Inverted spin Vs pr Knife edge gt 150 278 RER lt 10 sec Inverted flight gt Vs 225 417 ena ae 1 lt 2 min Particular caution must be exercised when performing maneuvers at speeds above V 174 KIAS 322 km h Large or abrupt control inputs with elevator and rudder above this speed may impose unacceptably high loads which exceed the structural capability of the aircraft Structure is designed for full and abrupt aileron input up to VNE For acrobatic maneuvers see chapter 4 All maneuvers can be performed in upright and inverted flight attitude 2 10 LOAD FACTORS Positive load factors Negative load factors Utility flight mrow 999 kg 2200 Ibs 4 4g 2g Acrobatic flight Mrow 850 kg 1874 Ibs 10g 10g Page 5 EASA approved Page date Chapter 02 24 01 2011 PT A Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 2 11 FLIGHT CREW LIMITS The minimum crew is 1 pilot f
8. aerobatic flight AVGAS 100 LL LEFT RIGHT 65 Liter 17 1 US gal 105 Liter 105 Liter XA42 1120 230 27 7 US gal 27 7 US gal 21130250 AVGAS 100 LL 65 Liter 17 1 US gal XA42 1120 230 On canopy frame rh XA42 1130 250 De 105 Liter o empty for ae Near canopy locking lever inside front and back Outside Canopy Lock 1 PULL lever to UNLOCK 2 LIFT canopy to OPEN XA42 1120 300 Page 7 EASA approved Page date Chapter 02 24 01 2011 Airplane Flight Manual XA42 rr AFM XA42 0040 002 A 01 On right cockpit wall For aircraft with Airspeed indicators in knots On baggage compartment Approved aerobatic maneuvers and recommended entry speeds OPEN Maneuver Min Entry Speed Max Entry Speed Aleron Rol okas 22skms Acro tank drain Wing tank drain XA42 1120 260 Baggage limited to max 10kg Compartment must be empty for aerobatic flight PS E Inverted Spin Stall J o 45 Climbing For aircraft with Airspeed indicators in km h OIL Min Max Sump 9 16 qts For oil grade refer to 8 Aircraft Flight Manual Approved aerobatic maneuvers and recommended entry speeds AAA 300038 E 3 Ss N Inverted Spin Stall Left wheelpant inner side Horizontal Line Stall 417 km h 45 Climbing 148 km h 417 km h Fuel Vent XA42 1120 261 Near vent fuselage underside 90 Up 185 km h 417 km h Vent Overflow Smoketank XA42 1120 271 Stall 417 km h Stall
9. as long as the transponder TRT 800H is installed Transponder Mode S according to ED73B Class 1 Level 2s Comm A B extd squitter For maximum flight level 35 000 ft maximum velocity 250 kts EASA approval number is EASA 210 269 and a Form 1 and A C address connector is part of the standard delivery Refer to latest edition of Funkwerk Avionics TRT 800H Operation Manual to get familiar with the TRT 800H Transponder 9 2 2 LIMITATIONS This aircraft must not be operated in controlled airspace if transponder is inoperative 9 2 3 EMERGENCY PROCEDURES To send an emergency signal Turn 7 7 0 O to switch the four digits of the standby Squawk Codes lower line Push vertical arrows to swap stand by and active emergency squawk 9 2 4 NORMAL PROCEDURES There are no changes to POH chapter 4 9 2 5 PERFORMANCE There are no changes to POH chapter 5 9 2 6 WEIGHT AND BALANCE Changes of CG and changes in empty weight are to be considered if the transponder is removed according to chapter 6 of this POH Funkwerk Avionics TRT 800 H 9 2 7 DESCRIPTION OF AIRCRAFT AND SYSTEMS Features Level 2es Class 1 Non Diversity Mode S Transponder providing downlink of aircraft information radio transmitter and receiver for ground radar interrogations on 1030 MHz and transmission of coded reply pulses to ground based radar on 1090 MHz Replies to ATCRBS interrogations using the ICAO 24 bit mode S address
10. date Chapter 03 24 01 2011 PT A Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 3 2 AIR SPEEDS FOR EMERGENCY OPERATION Stall speed 54 KIAS 100 km h Engine failure after takeoff Best recommended gliding speed glide angle 1 7 e Utility 999 kg e Acro 850 kg Precautionary landing with engine power Landing without engine power 80 KIAS 150 km h 80 KIAS 150 km h 80 KIAS 150 km h 80 KIAS 150 km h 80 KIAS 150 km h Maximum demonstrated cross wind component 25 kts 47 km h 3 3 OPERATIONAL CHECKLIST 3 3 1 ENGINE FAILURE DURING TAKEOFF When sufficient runway left Normal When insufficient runway is left Harsh APPLY BRAKES APPLY BRAKES Mixture PULL CUTOFF Ignition OFF Master switch OFF 3 3 2 ENGINE FAILURE IMMEDIATELY AFTER TAKEOFF Push stick to maintain 80 kts Mixture PULL CUTOFF Fuel selector switch OFF Ignition OFF Master switch OFF Straight ahead LAND 3 3 3 ENGINE FAILURE DURING FLIGHT RESTART ENGINE PROCESS Best glide speed 80 KIAS 150 km h Fuel capacity of tank selected CHECK Select to fullest tank SWITCH Ignition BOTH CHECK Page date 24 01 2011 Page 2 Chapter 03 Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 3 3 3 continued Engine restart in flight Propeller control Fine pitch Electric fuel pump Mixture Throttle 5 mm open Starter only if propeller is stopped 3 3 4 OIL SYSTEM MALFUNCTION Low oil pressure Changes in in
11. date Page VIII 24 01 2011 Airplane Flight Manual XA42 PT A AFM XA42 0040 002 A 01 1 GENERAL 1 1 DESCRIPTION The XA42 is a two seat high performance acrobatic tailwheel airplane The structure is manufactured from carbon honeycomb sandwich 1 2 SPECIFICATION OF CATEGORY The aircraft is certified in the Utility and Acrobatic category according to EASA CS 23 EASA type certificate data sheet A 507 1 3 MANUFACTURER XtremeAir GmbH HarzstraBe 2 Am Flughafen Cochstedt 39444 Hecklingen Germany Page 1 Page date Chapter 01 09 11 2010 png eI Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 1 4 TECHNICAL DATA 1 4 1 3 VIEW DRAWING 2542 2030 All dimensions in millimeters Page date Page 2 24 01 2011 Chapter 01 Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 1 4 2 MAIN DATA Length overall 6670 mm Height overall ground attitude 2542 mm Span 7500 mm Wheel base 4425 mm Wheel track 2000 mm 1 4 3 WING Wing plan form Trapezoid Wing span 7500 mm Wing area 11 25 m Aspect ratio 5 00 Airfoil PS 1 16 Tip PS 1 09 Root chord 2060 mm Tip chord 950 mm MAC 1505 mm Aileron span 3220 mm Aileron area 1 26 m Aileron deflection 30 1 4 4 HORIZONTAL TAIL INCLUDING ELEVATOR Plan form Trapezoid Span 2600 mm Area 2 97 m Airfoil DU86 MOD1 1 4 5 ELEVATOR Span 3200 mm Area 1 45 m Deflection 27 1 4 6 FLETTNER TAB Span 400 mm Tip chord 130 mm Deflection 30
12. ice build up select a suitable off airport landing field Page 5 Page date Chapter 03 24 01 2011 x gt 3 7 UNINTENTIONAL SPIN Standard procedure for spin recovery Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 Throttle IDLE Elevator and aileron NEUTRAL Rudder against direction of rotation APPLY After rotation stops Rudder NEUTRAL Aircraft RECOVER FROM DIVE 3 8 BAIL OUT Speed REDUCE below 100 kts Mixture PULL CUTOFF Canopy UNLOCK amp OPEN Straps OPEN Aircraft to the left LEAVE Parachute OPEN 3 9 EMERGENCY EXIT AFTER FLIP OVER Master switch OFF Fuel selector valve OFF Pull 8 Turn Seat belts OPEN Parachute harnesses when wearing a parachute OPEN Canopy handles PULL TO OPEN If canopy fails to open break with emergency escape tool EVACUATE ASAP 3 10 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 nose up and establish a shallow descend by adjusting throttle To flare gently increase power to bring the nose up to landing attitude Page date Page 6 24 01 2011 Chapter 03 Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 3 11 LIGHTNING STRIKE In case the aircraft gets struck by a lightning Engine Propeller Vibration Airspeed Load factors Controlability If satisfactory If not Pag
13. in front of the main spar of both sides of the wing Each can fit 105 L 27 7 US gal of fuel and can be flown down to 0 5 L in straight and level flight The total volume of the wing tanks is 210 L 54 4 US gal With 5 yaw Ya ball out and corresponding bank 0 5 L 0 13 US gal remain non usable The tanks all have their own filler cap with a diameter of 46 mm each Venting of the wing tanks is accomplished through a system that connects the wing tank vent hoses to the top of the acro tank Then the acro tank is vented through another vent hose which exits the fuselage to run along the left landing gear leg to the wheel cover where it is vented to the outside of the aircraft To drain the tanks they all have a flush drain valve located at the lowest point that allows appropriate drainage To avoid impurity there are filters installed at the pickup points of each tank and also there is a fuel filter in between the fuel selector valve and the fuel pump For security reasons an electrically driven auxiliary fuel pump is installed in addition to the mechanical driven fuel pump of the motor The pump has a bypass and is able to supply the motor at takeoff conditions It also can be used as a boost pump The switch is located on the righthand side electrical panel of the cockpit To indicate the amount of fuel there are probes installed in each tank The wing tank indicators use a float device potentiometer technology and the main tank has a ca
14. quantity e Maximum sump quantity 15 151 16 US at e Minimum sump quantity 8 521 9US qt Oil pressure e Minimum idling 1 7 bar 25 psi e Normal 3 8 6 5 bar 55 95 psi e Starting warm up taxi and takeoff 7 9 bar 115 psi It is normal for the oil pressure to flicker from 10 to 30 psi when going from upright to inverted flight During knife edge flights and zero G flights oil pressure may drop and the oil system may not scavenge resulting in engine failure or damage if flight is prolonged Knife edge and zero G flight should not exceed 10 seconds If oil pressure drops to 0 psi O kPa the propeller pitch changes automatically to coarse high pitch with a corresponding decrease in RPM Apply positive g loads to avoid engine stoppage Fuel pressure Inlet to fuel injector Maximum 4 48 bar 65 psi e Minimum 2 00 bar 29 psi e Minimum idle 0 83 bar 12 psi Cylinder head temperature Maximum 240 C 465 F Page 2 Page date Chapter 02 24 01 2011 Airplane Flight Manual XA42 png mE AFM XA42 0040 002 A 01 2 5 PROPELLER MT Propeller MTV 9 B C C203 20d 3 blade hydraulic constant speed RPM limits Max takeoff Acrobatic 2700 rpm Utility 2670 rpm Max continuous 2500 rpm 2 6 WEIGHT LIMITS Maximum empty weight e Utility 670 kg 1477 lbs e Acro 670 kg 1477 lbs Maximum take off weight e Utility 999 kg 2200 Ibs e Acro 850 kg 1874 Ibs Maximum landing weight e Utility 999 kg 2200 lbs e Acro 85
15. six cylinder horizontally opposed air cooled direct drive fuel injection engine type with inverted oil system For the present TBO refer to latest issue of Textron Lycoming service letters The AEIO 580 B1A engine is equipped with special counterweights The power plant installation includes the following accessories e Alternator B amp C SD 20 e Fuel Injector Bendix RSA 10AD1 e Fuel pump Weldon Pump 8120 G e Magnetos Slick 6350 6393 e Propeller governor MT Propeller P 880 5 Starter B amp C BC315 100 2 e Voltage regulator B amp C LR3C 14V 4A The engine is operated with the following manual controls e Throttle control e Fuel mixture control e RPM control The propeller governor monitors the RPM automatically and prevents overspeeding In the event that oil pressure is lost the propeller is automatically adjusted to coarse pitch in order to avoid overspeeding The use of 100 130 aviation grade fuel AvGas 100 is the minimum grade recommended by the manufacturer of the AEIO 580 B1A engine Page date Page 6 24 01 2011 Chapter 07 Airplane Flight Manual XA42 T EU 7 10 2 OIL SYSTEM The oil is cooled by a two oil coolers mounted on the left and right hand side in the engine compartment The oil level is determined by a dipstick A thermostatic valve is fitted upstream of the oil cooler This valve ensures a quick warmup of the oil after engine start Oil capacity and grades Maximum sump quantity 15 15 L 16
16. via hoses weld on type injectors on the two tail pipes of the exhaust system Inline between the pump and the injectors is an electric shutoff valve mounted on the firewall The electric circuit of the pump is secured via a circuit breaker switch on the right hand console the smoke ON OFF switch is on the left hand side console on top of the throttle lever When the smoke system is switched ON and direction is switched to SMOKE the pump is switched on the valve opens and the system is injecting smoke oil in the exhaust To fill the system the refill hose s end with the male connector plug is connected to the female connector plug behind the pilot s seat the loose end of the refill hose put in the smoke oil reservoir The pump direction switch needs to be in position REFILL and ON then the valve remains closed the polarity of the pump is reversed and the pump feeds the smoke oil into the smoke tank The tank is full when smoke oil starts to pour from the smoke tank ventline on the bottom of the fuselage Then the smoke switch must be turned OFF and the pump direction switch returned to SMOKE Page date Page 10 24 01 2011 Chapter 07 Airplane Flight Manual XA42 png mE AFM XA42 0040 002 A 01 Intentionally left blank Page 11 Page date Chapter 07 24 01 2011 T A Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 8 HANDLING SERVICE 8 MAINTENANCE 8 1 INTRODUCTION a The airplane owner
17. wing tank every 30 min 4 9 LANDING PROCEDURES 4 9 1 DESCENT Mixture Fuel selector valve to acrobatic tank ACRO Electric fuel pump Power during descent RPM min 2000 rpm Manifold pressure Watch CHT to prevent excessive cooling Airspeed 4 9 2 PRE LANDING Straps Mixture Fuel selector valve to ACRO tank Propeller control Approach speed Page 7 Chapter 04 ME ADJUST ADJUST AS REQUIRED 120 kts 220 km h 90 kts 167 km h 78 kts 144 km h ADJUST AS REQUIRED ADJUST SWITCH PUSH FULL RICH SWITCH ON ADJUST AS REQUIRED AS REQUIRED TIGHTEN PUSH FULL RICH SWITCH PUSH FINE PITCH 80 kts 150 km h Page date 24 01 2011 Ah 4 9 3 GO AROUND Throttle Airspeed 4 9 4 NORMAL LANDING Approach speed Three point attitude Elevator pulled 4 9 5 LANDING IN CROSSWIND Approach speed On main wheels Elevator pulled Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 FULL OPEN 80 kts 150 km h 80 kts 150 km h TOUCHDOWN DECELERATE 80 kts 150 km h TOUCHDOWN BRAKE The maximum demonstrated crosswind component for take off and landing is 25 kts 47 km h 4 9 6 SHORT FIELD LANDING Approach speed throttle idle Approach speed with power Three point attitude Brakes 4 9 7 AFTER LANDING Electrical fuel pump Elevator pulled 4 10 SHUTDOWN Throttle Avionic Switch Mixture Ignition Master Switch 80 kts 150 km h 70 kts 130 km h TOUCHDOWN APPLY as ne
18. y sus 6 02 2 12 KINDS OF OPERATIONAL LIMITS uuesenssnnnnnnnnnnnnnnnnnnnnnnnnannnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnn 6 02 2 13 MAXIMUM OPERATING ALTITUDE tt nln i eee nn ncn i een nn rra nr sasha sassa 6 02 2 14 TYRE PRESSURE cocina e stdeeaieeseiatecetiecisecrerseeess 6 02 2 15 SMOKE Olla ie 6 02 2 16 MARKINGS AND PLACARDS ll lr nnn ss sasaqa suwas qa aqa sassa aiaa 6 02 2 17 KINDS OF OPERATION EQUIPMENT LIST I n nsn 10 02 3 EMERGENCY PROCEDURES U U U u Q Q 1 03 31 INTRODUCTION cdt tds 1 03 3 2 AIR SPEEDS FOR EMERGENCY OPERATION eer eer ns n 2 03 3 3 OPERATIONAL CHECKLIST u a aada aiaia 2 03 3 4 FORGED LEANDINGS 332er 4 03 B29 FIRES iia A e A A A 5 03 3 6 ICING INADVERTENT ENCOUNTER ccccccononococccncnnnnnnnancnnnnnenennnnnanancrnnrnnnnnnnanancrnnnnnes 5 03 3 7 INITENTIONAL SPIN siria 6 03 3 8 BAM OUT a a 6 03 3 9 EMERGENCY EXIT AFTER FLIP OVER unensnsnnasnannannensnnnnnnnnnannnnnannnnnnnnnnnnnnnannnnnnnannnnnnn 6 03 3 10 ELEVATOR CONTROL FAILURE 0 i nn i een noni nr nrrrrrnrn rn rnnn naar 6 03 3 11 LIGHTNING STRIKE coccion een 7 03 4 NORMAL PROCEDURES U U U u u u u Q 1 04 Bids GENERA C S S usut AEE N 1 04 4 2 PREFLIGHT INSPECTION coi id italia 1 04 Page IV Page date 24 01 2011 ram U Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 4 3 CHECKLIST PROCEDURES
19. 0 0 20 R 2 Main Wheel and Brake Assy Beringer Kit Nr 3A 01 1 00 0 12 R 2 Main Wheel Tires Michelin Aviator 5 00 5 1 20 0 12 R 1 Tail Wheel Assy XtremeAir GmbH XA42 3220 051 2 00 4 80 R 1 Tail Wheel Continental 105 45 65 0 25 4 80 R 1 Smoke Switch Conrad 646H 0 03 1 50 R 1 Trim Switch Conrad 647H 0 03 1 39 R 1 Ignition Switch ACS Products A 510 2 0 06 1 40 R a s 3130 FIIO P7TI 5 Circuit Breaker Switches E T A W12QYZ 0 03 1 45 R 9 Circuit Breaker E T A 7277 2 div 0 02 1 25 R 1 Main Bus Fuse Holder Sinus live SH 150 0 05 1 20 R 1 Battery Enersys Energy Genesis EP 6 10 0 27 R 1 Fuel Capacity Indicator Westach A3T13 0 19 1 20 R 1 Fuel Probe Main Tank Westach 395 5S 1B 0 15 0 05 R 2 Fuel Probe Wing Tank VDO 226 801 015 001G 0 20 0 35 R 1 Fuel Selector Valve Andair FS 20x5 MB 0 12 1 40 R Page date Page 5 24 01 2011 EASA approved Chapter 06 Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 rama Qty Item Manufacturer Part or PN Er nl Oo 1 Ampere Shunt Westach 237 30 0 09 1 15 R 1 Tachometer Noris Automation NIR2 060 FG 476 0 15 1 15 R 1 RPM Sensor JPI 420815 1 0 05 0 18 R 1 ete oe ar Airpath C 2300 0 25 1 15 R ei er eas Westach 2DA3 249KV 0 08 1 15 R a oe BR Westach 387 150KV 0 12 0 13 R 1 poe ie Falcon Gauges GM510 2 0 36 1 15 R 1 Clock Timer ADI CT60 0 07 1 15 R 1 j a Winter 6FMS 533 0 22
20. 0 002 A 01 Tyre wear CHECK G Right rear fuselage Fuselage skin for damage CHECK Static port clean CHECK H Right wing trailing edge Spade and spade arm CHECK Aileron linkage CHECK Wing trailing edge and skin for damage CHECK Aileron trailing leading edge and skin for damage CHECK Aileron hinges CHECK Freedom of movement and play CHECK 1 Right wing leading edge Wing leading edge and skin for damage CHECK Fuel cap and fuel capacity CHECK Right wing tank DRAIN WATER J Right main gear Main gear strut to damage CHECK Tyre to pressure and wear CHECK Tire and wheel slip mark CHECK K Right front fuselage Fuselage skin for damage CHECK L Engine Oil quantity CHECK All items of this check below this line must be performed every 20 Flights Cowling OPEN Engine core to cracks CHECK Baffling to cracks CHECK Engine mount to cracks CHECK Exhaust system to cracks CHECK Exhaust system fixtures CHECK Cables and hoses to chafing CHECK Pae3 Pagedate Chapter 04 24 01 2011 Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 Ignition cables and spark plugs Wiring Engine actuator cables to freedom of movement Oil and fuel system for leaks Cowling M Propeller Blades to damage Hub to damage and oil leaks Play of blades in hub N Left front fuselage Fuselage skin for damage O Canopy Canopy frame and glass to damage P Left main gear Main gear strut to damage Tyre to pressure and wear Ti
21. 0 kg 1874 Ibs 2 7 WEIGHT AND CENTER OF GRAVITY ENVELOPE Reference planes for CG calculations e vertical firewall e horizontal straight part of cockpit frame 2 7 1 UTILITY FLIGHT Maximum takeoff Forward CG Rear CG weight 999 kg 2200 Ibs 550 mm 21 65 in 25 700 mm 27 55 in 33 2 7 2 ACROBATIC FLIGHT Admin takeoff Forward CG Rear CG weight 850 kg 1874 Ibs 550 mm 21 65 in 25 700 mm 27 55 in 33 2 8 BAGGAGE Maximum allowable baggage is 10 kg 22 Ibs securely stowed in the baggage compartment behind the pilot s seat Page 3 EASA approved Page date Chapter 02 24 01 2011 Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 2 9 ACROBATIC MANEUVERS 2 8 1 UTILITY FLIGHT All acrobatic maneuvers are prohibited except the following 2 8 2 ACROBATIC FLIGHT ME e Stall e Chandelle e Lazy eight e Steep turns The airplane is certified in the acrobatic category and capable of unlimited acrobatics The wing tanks and the baggage compartment must be empty for all acrobatic flights Inverted maneuvers are limited to a maximum time of 2 minutes The recommended basic maneuver entry speeds are listed below Recommended entry speeds IAS Maneuvers Symbol Remarks Min kts km h Max kts km h Horizontal line Vs 225 417 I Aileron Roll Vs 225 417 I 45 climbing 80 148 225 417 WA 90 up
22. 2 0040 002 A 01 Instrument Position Standard Optional Air speed indicator 1 x Magnetic direction indicator 2 x Altimeter 3 x Tachometer 4 x Oil temperature oil pressure 5 x EGT scanner 6 x Manifold pressure 7 x Fuel pressure 8 X Volt Ampere meter 9 x G Meter 10 x Clock 11 X Prop 12 x Mixture 13 x Radio 14 x Transponder 15 x Fuel capacity indicator 16 x Fuel Selector Valve 17 x Throttle Friction 18 x Elevator trim switch 19 x Elevator trim indicator 19b x Throttle with smoke ON OFF switch 20 amp 21 x Smoke pump circuit breaker switch 22 x Avionic Master circuit breaker switch 23 x ACL circuit breaker switch 24 x Electric fuel pump circuit breaker switch 25 x Split Master Switch Battery Gen 26 x Ignition key 27 x Circuit breakers 28 X PTT button 29 x ELT Remote Switch 30 x Page date Page 4 24 01 2011 Chapter 07 png en EU Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 Fig 7 6 3 Instrument Panel front Instrument Position Standard Optional Air speed indicator 1 x Magnetic direction indicator 2 x Altimeter 3 x Throttle 4 x PTT button 5 x 7 7 LANDING GEAR Landing gear is a taildragger configuration made out of spring steel Tail wheel is a swivel mounted solid rubber wheel Main landing gear wheels have a size of 5 00 Main la
23. 4 01 2011 Chapter 02 Airplane Flight Manual XA42 png a Eh VE AFM XA42 0040 002 A 01 ge 2 17 2 OPERATING PLACARDS Callsign placard on the instrument panel example only On right cockpit wall Near eyeball air vents ERXA No Smoking E XA42 1130 200 a No Smoking 210 A 1130 320 On right cockpit wall Below compass The aircraft must be operated in accordance with the for n 30 60 120 150 Aircraft Flight Manual and the certification categories steer of the aircraft to which the placards apply ror s 210 240 w 300 330 XA42 1130 340 DATE VHF ON OFF AIRPATH On right cockpit wall This aircraft is certified for day VFR flights in non icing conditions Wearing parachutes is mandatory Solo flying from rear seat only If structural temperature exceeds 72 C flying is prohibited XA42 1130 220 Behind pilot seat and On instrument panel front instrument panel Spin Recovery Headset Spin recovery must be initiated when spiral characteristics appear or after a maximum of 6 turns 1 Reduce power to idle and center stick 2 Apply and hold rudder opposite to direction of rotation hard pedal until rotation stops 3 Return to level flight XA42 1130 350 On fuel quantity indicator Near fuel filler caps ACRO 65 Liter ae 104 KEN 17 1 US gal eo E 770 4 Takeoff Landing xV 0 on ACRO only Wing tanks must be empty for
24. 4 27 2974 67 150 39 62 108 239 10 36 72 3187 15 160 42 27 115 2 253 97 39 17 3399 63 170 44 91 122 4 269 85 41 62 3612 10 180 47 55 129 6 285 72 44 06 3824 58 190 50 19 136 8 301 59 46 51 4037 06 200 52 83 144 0 317 46 48 96 4249 53 210 55 47 152 2 335 54 51 41 4462 01 Smoke Tank Baggage Arm 2 62 m 103 15 in Paraffin density 0 85 Liter US Gallons Kg Ibs Kg xm inch x Ibs 5 2 64 4 25 9 37 12 37 1073 45 10 5 28 8 5 18 74 24 74 2146 90 15 7 92 12 75 28 11 37 10 3220 35 20 10 56 17 0 37 48 49 47 4293 80 25 13 20 21 25 46 85 61 84 5367 25 28 15 85 23 8 52 47 69 26 6011 32 Page date Page 3 24 01 2011 EASA approved Chapter 06 pnp A Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 6 5 WEIGHTS AND MOMENTS LIMITS WEISHT KG lbs 1000 2205 tity 750 2074 900 1984 MTOW 850 1874 ACRO 800 1764 750 1654 700 1544 EM PTY 650 1433 WEIGHT ARM CM 50 19 7 55 21 7 60 23 6 65 25 6 70 27 6 ARM INCH Example At 900kg 1984 Ibs and 56700 kgcm 49203 in Ibs CG Location is 63 cm 24 8 in aft of Reference Datum UTILITY FLIGHT Masia takeoff Forward CG Rear CG weight 999 kg 2200 Ibs 550 mm 21 65 in 25 700 mm 27 55 in 33 ACROBATIC FLIGHT maximum takeoff Forward CG Rear CG weight 850 kg 1874 Ibs 550 mm 21 65 in 25 700 mm 27 55 in 33 Page date Page 4 24 01 2011 EASA approved Chapter 06 Fag a Airplane Flight Man
25. 417 km h On left rear cockpit wall near G Meter low RPM lt Prop B gt high RPM Maximum G Loads lean lt lt Mixture p gt rich Aerobatic 10G Mrow 850kg XA42 1130 330 Utility 4 4G 2 0G M ow 999kg XA42 1120 Near smoke refill connector SMOKE OlL Capacity 27 Liters For oil grade refer to El Aircraft Flight Manual XA42 1130 210 Under the Airspeed indicator Vo 174 KIAS XA42 1130 355 Page 8 Page date Chapter 02 24 01 2011 Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 2 17 3 INSTRUMENT MARKINGS Airspeed indicator green arc yellow arc red line Oil pressure indicator red line yellow arc green arc yellow arc red line Oil temperature indicator green arc red line Fuel pressure indicator yellow arc green arc red line Manifold pressure indicator green arc Cylinder head temperature indicator Operating Range eS 54 kts 99 km h to 185 kts 342 km h 185 kts 342 km h to 225 kts 417 km h 225 kts 417 km h 25 psi 25 psi to 55 psi 55 psi to 95 psi 95 psi to 115 psi 115 psi 100 F to 245 F 245 F 0 psi to 12 psi 12 psi to 65 psi 65 psi 11 in Hg to 32 in Hg 200 F to 465 F Starts to flicker when exceeding max temperature Tachometer green arc 700 rpm to 2500 rpm yellow arc 2500 rpm to 2700 rpm red line 2700 rpm G Meter Acrobatic MToW 850 kg 10g Utility MToW 999 kg 4 4g 2 0g Page 9 EASA approved Page date Ch
26. E 60 SAE 60 gt 16 C 60 F SAE 50 SAE 40 or SAE 60 1 C to 32 C 30 F to 90 F SAE 40 SAE 40 18 C to 21 C 0 F to 70 F SAE 30 SAE 30 SE 40 or 20W50 18 C to 32 C 0 F to 90 F SAE 20W50 SAE 20W50 or SAE 15W50 lt 12 C 10 F SAE 20 SAE 30 or 20W30 Single or multi viscosity aviation grade oils see latest issue of Textron Lycoming S I No 1014 1 10 SMOKE OIL Smoke Oil type Straight paraffin oil viscosity 30 50 cts at 20 C 68 F initial boiling point gt 330 C 626 F For example Fauth FC05 Texaco Canopus 13 or equivalent Total Smoke Oil capacity 28 7 4 US gal 1 11 LOADING Utility Category Acrobatic Category Wing Loading kg m 84 4 75 5 Power Weight Ratio kg hp 3 01 2 69 1 12 TERMINOLOGY Air Speeds CAS Calibrated air speed CAS TAS in standard atmospheric conditions at sea level IAS Indicated air speed KIAS Indicated air speed in knots TAS True air speed same as CAS compensated for altitude temperature and density Va Maneuvering speed Vne Never exceed speed VNo Maximum structural cruising speed Vs Stalling speed minimum steady flight speed Vx Best angle of climb speed Vy Best rate of climb speed Meteorological Terminology ISA International standard atmospheric condition OAT Outside air temperature Page date Page 5 24 01 2011 Chapter 01 pnp A Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 Secondary Terminology fpm
27. P a Airplane Flight M I S N Manufacturer XtremeAir GmbH Registration Harzstra e 2 Am Flughafen Cochstedt 39444 Hecklingen Germany Document Number AFM XA42 0040 002 A 01 This Manual includes the material required to be furnished to the pilot by EASA regulations and additional informations provided by the manufacturer and constitutes the EASA approved Flight Manual This Flight Manual is EASA approved under Approval Number A 507 EASA certification manager Cover WE Airplane Flight Manual XA42 RT LH AFM XA42 0040 002 A 01 Intentionally left blank Page l Page date 24 01 2011 mE Ts Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 LOG OF REVISIONS Issue Date Approved A 01 27 01 2011 Page date Page II 24 01 2011 PT A Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 LOG OF EFFECTIVE PAGES Issue Cover and A 01 II and III A 01 IV and V A 01 VI and VII A 01 VIII and Chapter 01 Page 1 A 01 Chapter 01 Page 2 and Chapter 01 Page 3 A 01 Chapter 01 Page 4 and Chapter 01 Page 5 A 01 Chapter 01 Page 6 and Chapter 01 Page 7 A 01 Chapter 01 Page 8 and Chapter 02 Page 1 A 01 Chapter 02 Page 2 and Chapter 02 Page 3 A 01 Chapter 02 Page 4 and Chapter 02 Page 5 A 01 Chapter 02 Page 6 and Chapter 02 Page 7 A 01 Chapter 02 Page 8 and Chapter 02 Page 9 A 01 Chapter 02 Page 10 and Chapter 02 Page 11 A 01 Chapter 02 Page 12 and Chapte
28. PPERRFPFERFPFERRFFFERFPERFPFERRFFEEERERFERREFFERERFEREUFEERREEREFFEREUFERRERFERERFERERFRFERRRFERRERFERRRFERRR VI X 02 u I PERPPPRERPRFERERFEERFFFERPFEREPFEREFFFERERFERRREFFEREFFEREUFEERERFERRREREUFEERERFEREUFEEREFFEREEEEEEREREEERRFEREUFERERRFRRRFERRR VI WARNINGS CAUTIONS AND NOTES U U U u u VII 1 GENERAL U U U U U u u u u u u 1 01 1 1 DESCRIPTION cosita 1 01 1 2 SPECTICATION OF CATEGORY iii 1 01 1 3 MANUFACTURER coat iii 1 01 1 4 TECHNICAL DATA iii 2 01 15 ENGINE tidad oct Yau 4 01 156 PROPELLER ee Ada 4 01 1 7 EXHAUST SYSTEM ne id 4 01 1 9 FUEL een 4 01 AAA en o yau tite oaa uqa cite iine ected 5 01 ELO SMOKE OIE ar E E kaa a toledo 5 01 1711 LOADING tad 5 01 1 12 TERMINOLOGY Ciria da 5 01 1 13 CONVERSI N TABLE oo ii 7 01 2 LIMITATIONS eee ee 1 02 2 1 GENERAL ocupa ia 1 02 22 AIRSPEED IAS osecccclesecces execasticcessvecdnusswnceussazesesnvndsiedcichsseuechvesczectasnenacsennudioensbiee 1 02 2 3 CROSSWIND COMPONENT wiiscvcchetseestseaeczceseeuecstentees cece dawesssnecdeccaebavesssseeescreqaseiserzeesee 1 02 24 ENGINE Su o 2 02 2 5 PROPELLER O ya q O 3 02 2 6 WEIGHTILIMITS 200 3 02 2 7 WEIGHT AND CENTER OF GRAVITY ENVELOPE a n 3 02 28 BAGGAGE cut Bene 3 02 2 9 ACROBATIC MANEUVERS nn en ee an anne 4 02 2 10 LOAD FACTORS ire u a a 2 iio ida 5 02 2 11 FLIGHT CREW LIMITS au 2 ee ee een
29. Page 3 Page date Chapter 01 24 01 2011 Ka Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 1 4 7 Plan form Height Area Airfoil 1 4 8 RUDDER Height Area Deflection 1 5 ENGINE Manufacturer Type Rated power Acrobatic Rated power Utility 1 6 PROPELLER Manufacturer Type 1 7 EXHAUST SYSTEM Manufacturer Type 1 8 FUEL Fuel type Total fuel capacity e Wing tanks e Acro tank Usable fuel capacity Total Usable fuel capacity Acro Page 4 Chapter 01 MA VERTICAL TAIL INCLUDING RUDDER Trapezoid 1100 mm 1 54 m2 DU86 MOD1 1400 mm 0 82 m2 302 Lycoming Engines Williamsport PA 17701 USA AEIO 580 B1A 235 kW 315 hp 2700 rpm 233 kW 312 hp 2670 rpm MT Propeller Entwicklung GmbH 94348 Atting Germany MTV 9 B C C203 20d Gomolzig GmbH EisenwerkstraBe 9 58332 Schwelm Germany 3 in 1 each side Aviation Gasoline Avgas 100LL For alternative fuel grades see latest issue of Textron Lycoming S I No 1070 Minimum Maximum 100 130 octane 275 1 72 5 US gal 2x 1051 2 x 27 7 US gal 65 17 1 US gal 273 72 0 US gal 64 16 9 US gal Page date 24 01 2011 Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 1 9 OIL Maximum sump capacity 15 15 16 US qt Minimum sump capacity 8 52 9 US qt Average Ambient Air Temp Mil L6082 grades Mil 22851 ashless dispersant grades All temperatures SAE 15W50 or 20W50 gt 27 C 80 F SA
30. Page 9 Page date Chapter 04 24 01 2011 pnp A Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 4 12 2 MANEUVERS Utility category Stall Level and accelerated stalls up to MTOW Airspeed and G limits in the Utility category are to be respected Chandelle Airspeed and G limits in the Utility category must be respected Lazy eight Airspeed and G limits in the Utility category must be respected Steep turns Airspeed and G limits in the Utility category must be respected Acrobatic category Horizontal line A horizontal line can be flown with any required speed between Vs und Vye 45 Climbing line With max continuous power the aircraft can sustain this line The speed will not drop below 80 kts 144 km h 90 Vertical climbing line A vertical climbing line can be entered with any required speed between Vs und Vue In long zero g lines the propeller can go in high pitch due to a loss of oil pressure By applying any g load the oil pressure will be restored 45 Descending line Reduce power to prevent exceeding Vue 90 Vertical descending line Reduce power to prevent exceeding Vne Snap roll Snap rolls must not be flown above 174 kts 322 km h Aileron roll Full aileron deflection rolls can be flown up to 225 kts 417 km h Vye Quarter looping upwards Recommended minimum entry speed is 100 kts 185 km h If another maneuver shall follow in the vertical line more speed is required A full round loop requir
31. Pilot rear seat Copilot front seat Weight Occupant Parachute Arm 1 73 m 68 1 in Arm 0 86 m 33 86 in Moment kg Ibs Kg xm in x Ibs Kg x m inch x Ibs 55 121 95 15 8258 64 47 30 4105 45 60 132 103 80 9009 42 51 60 4478 67 65 143 112 45 9760 21 55 90 4851 90 70 154 121 10 10511 00 60 20 5225 12 75 165 129 75 11261 78 64 50 5598 34 80 176 138 40 12012 57 68 80 5971 56 85 187 147 05 12763 35 73 10 6344 79 90 198 155 70 13514 14 77 40 6718 01 95 209 164 35 14264 92 81 70 7091 23 100 220 173 00 15015 71 86 00 7464 46 110 242 190 30 16517 28 94 60 8210 90 Fuel Acro Tank Arm 0 285 m 11 22 in Avgas density 0 72 Liter US Gallons Kg Ibs Kg xm inch x Ibs 10 2 64 7 2 15 87 2 05 178 06 20 5 28 14 4 31 75 4 10 356 24 30 7 92 21 6 47 62 6 16 534 30 40 10 56 28 8 63 49 8 21 712 36 50 13 20 36 79 36 10 26 890 42 60 15 85 43 2 95 24 12 31 1068 59 65 17 17 46 8 103 18 13 34 1157 68 Fuel Wing Tanks Arm 0 34 m 13 38 in Avgas density 0 72 Liter US Gallons Kg Ibs Kg xm inch x Ibs 10 2 64 7 2 15 87 2 45 212 48 20 5 28 14 4 31 75 4 90 424 95 30 7 92 21 6 47 62 7 34 637 43 40 10 56 28 8 63 49 9 79 849 91 50 13 20 36 79 36 12 24 1062 38 60 15 85 43 2 95 24 14 69 1274 86 70 17 17 46 8 103 18 17 14 1487 34 80 21 13 57 6 126 99 19 58 1699 81 90 23 77 64 8 142 86 22 03 1912 29 100 26 41 72 0 158 73 24 48 2124 77 110 29 06 79 2 174 61 26 93 2337 24 120 31 70 86 4 190 48 29 38 2549 72 130 34 34 93 6 206 35 31 82 2762 20 140 36 98 100 8 222 22 3
32. WR Endurance ft C C 1 min Hg kts h min NM 4 000 9 9 2100 21 0 167 5 30 4 000 9 9 2300 23 0 178 4 000 9 9 2400 24 0 185 10 000 5 5 2000 20 0 179 10 000 5 5 2400 21 0 210 Page date Page 6 24 01 2011 Chapter 05 Airplane Flight Manual XA42 png A AFM XA42 0040 002 A 01 5 8 LANDING PERFORMANCE The mentioned landing distances are valid for a hard surface runway clean aircraft and no wind For other conditions use following factors Wind 10 kts headwind distances are reduced by 15 20 kts headwind distances are reduced by 30 for each 3 kts tailwind distances are increased by 10 Runway Distances on a dry hard grass runway are 10 longer For wet soft and uneven fields factors must be determined individually by the PIC Landing distances 999 kg Landing weight Pressure altitude Temperature C ft pian S ISA 10 ISA 20 ISA 30 ra u 0 SL om ee 1000 a EE 2000 S ag E 3000 1065 667 694 721 1065 ng HE 5000 og E 6000 Eg 7000 KW s 8000 496 823 515 854 534 886 554 919 575 954 597 991 620 644 670 667 eas es _ lem m C em Page 7 Page date Chapter 05 24 01 2011 T EIU Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 I 850 kg Landing weight Pressure altitude Temperature C SA ft I PR Landing run 0 SL over 50 ft obstacle Bs Landing run 1000 over 50 ft obstacle FG Landing run 2000 over 50
33. all is vertical d There are two engine hoists provided on the top of the engine which can be used to lift the airplane with a crane Tail wheel resting on ground 8 7 CLEANING AND PROTECTION For cleaning the aircraft use clean water and an automotive paint cleaner Use only clear warm water and special clean leather Use a leather to dry the surfaces Never dry wipe the canopy glass Never use fuel alcohol aceton etc to clean the canopy Page 2 Page date Chapter 08 24 01 2011 Airplane Flight Manual XA42 png an EU AFM XA42 0040 002 A 01 Intentionally left blank Page 3 Page date Chapter 08 24 01 2011 Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 9 SUPPLEMENTS LOG OF EFFECTIVE PAGES Chapter 09 Page I and Chapter 09 Page 1 1 Chapter09 Page 2 1 and Chapter 09 Page 2 2 TABLE OF CONTENT Ah Issue A 01 A 01 Supplement Title Installed No EMERGENCY LOCATION TRANSMITTER 9 1 TRANSPONDER TRT 800 H 9 2 Page Page date Chapter 09 24 01 2011 Airplane Flight Manual XA42 T Ts AFM XA42 0040 002 A 01 9 1 EMERGENCY LOCATION TRANSMITTER 9 1 1 GENERAL Emergency Location Transmitter ELT intalled is the Kannad 406 AF COMPACT This supplement is a permanent part of the handbook and must be used as long as ELT is installed ELT is self powered by the ELT battery replacement every 6 years ELT powered remote switch eliminat
34. als which also include the brake function The control cable leads directly to the lever inside the rudder The limit stops of the control system are attached to this lever The deflection is 30 7 5 5 SECONDARY CONTROL The elevator trim is a flettner trim system An electrical linear drive moves a lever that acts as a positioner for a servo flettner tab The electric motor is operated by a toggle switch on the lefthand sidepanel and cut off by means of limit switches in the respective end positions The trim position is picked up electrically by a potentiometer and displayed by a series of LEDs The canopy lock is operated from the outside by pulling the handle on left side of the canopy Inside a handle is located in the cockpit used for locking as well as for normal operation and for emergency release The starter magneto switch is located on the righthand sidepanel Page date Page 2 24 01 2011 Chapter 07 Airplane Flight Manual XA42 png A AFM XA42 0040 002 A 01 7 6 INSTRUMENTATION 7 6 1 INSTRUMENT PANEL For instrumentation of the instrument panel refer to the following figure The table below shows whether the instruments are standard or optional equipment Fig 7 6 1 cockpit Oon 12 47 16 ee 922 913 OC EGT CHT COM XPDR O ELEVATOR TRIM lt O O cO 0 amp 21 Page 3 Page date Chapter 07 24 01 2011 T Ts Airplane Flight Manual XA42 AFM XA4
35. apter 02 24 01 2011 png ET UE Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 2 18 KINDS OF OPERATION EQUIPMENT LIST The aircraft may be operated under VFR day conditions when the appropriate equipment is installed and operable If icing conditions occur flying is prohibited To meet certification standards the following equipment and systems must be installed and operable Utility Acrobatic 1 seat 2 seats Communication 1 Transceiver VFH O O O 2 Emergency Locator Transmitter M M M Electrical Power 1 Battery M M M 2 Alternator O O O 3 Amperemeter O O O Flight Control System 1 Elevator trim control M M M Fuel 1 Boost pump M M M 2 Fuel quantity indicator M M M 3 Manifold pressure M M M 4 Fuel flow indicator O O O 5 Fuel pressure M M M Light 1 Anti collision light M M M Navigation 1 Altimeter M M M 2 Airspeed indicator M M M 3 Magnetic direction indicator M M M 4 OAT indicator O O O 5 Vertical speed indicator O O O 6 Turn and bank indicator O O O 7 Artificial horizon O O O 8 Directional gyro O O O 9 Transponder O O O Engine Control 1 RPM indicator M M M 2 Exhaust gas temperature indicator O O O 3 Cylinder head temperature indicator O O O Oil 1 Oil temperature indicator M M 2 Oil pressure indicator M M M Page date EASA approved Page 10 24 01 2011 Chapter 02 Airplane Flight Manual XA42 i A AFM XA42 0040 002 A 01 continu
36. ay 7 13 CABIN ENVIRONMENT CONTROL To ensure a comfortable climate and fresh air supply inside the cabin the aircraft is equipped with a ventilation system in the canopy frame The right NACA inlet in the canopy frame feeds the canopy defog system it is actuated by a lever on the righthand side of the canopy frame The two eyeball airvents are fed by the left NACA inlet can be opened closed from the pilot s seat from the front sear they can be individually adjusted by turning the front rim Page 9 Page date Chapter 07 24 01 2011 PT A Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 7 14 BAGGAGE COMPARTMENT The baggage compartment is located behind the seat and may carry up to 10 kg 22 Ibs of secured baggage The baggage compartment must be empty during acrobatic flying Before loading the baggage compartment check CG limits are not exceeded according to weight 8 balance calculation 7 15 PITOT STATIC SYSTEM Total pressure is taken from a pitot tube mounted on the lefthand wingtip Static pressure is taken from static ports on both fuselage sides between the wing trailing edge and the stabilizer leading edge Airspeed indicator and altimeter are attached to these pressure lines 7 16 SMOKE SYSTEM The smoke system consists of a carbon fiber tank with 27 L 7 13 US gal capacity located behind the pilots seat The tank is equipped with a flop tube In front of the smoketank is an electric pump which feeds
37. dication of oil temperature and oil pressure Power When oil pressure drops below 25 psi engine must be stopped PUSH ON PUSH FULL RICH ADJUST ENGAGE OBSERVE REDUCE If oil pressure drops to zero Propeller goes to high pitch low RPM low drag High oil temperature Oil pressure When oil temperature rises and oil pressure sinks If possible 3 3 5 ALTERNATOR FAILURE AND WIRE FIRE Alternator failure Alternator switch Before next flight Wire fire Master switch After fire extinguished Fire keeps burning Page 3 Chapter 03 CHECK REDUCE POWER INCREASE airspeed OFF SOLVE PROBLEM OFF LAND ON NEAREST AIRFIELD LAND IMMEDIATELY Page date 24 01 2011 x gt 3 3 6 ENGINE MALFUNCTIONS High cylinder head temperature Mixture Power Flight with reduced power Sudden loss of power Mixture Electric fuel pump Fuel capacity of tank selected Select to fullest tank Ignition BOTH Constant speed propeller Malfunctions Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 PUSH FULL RICH REDUCE CONTINUE PUSH FULL RICH ON CHECK SWITCH CHECK CHECK if necessary PUSH Fine pitch Power REDUCE Engine instruments CHECK Problem ANALYSE As soon as possible LAND 3 4 FORCED LANDINGS 3 4 1 EMERGENCY LANDING WITHOUT ENGINE POWER Glide with engine off Recommended glide speed Propeller Best glide ratio 80 KIAS 150 km h PULL COARSE PITCH E 7 Prop at fine pitch pu
38. e O By using a plumb bob mark the tail wheel s axle center Tail wheel must be aligned straight D Measure distance from reference plane to main wheel axles Arm A distance from reference plane to tail wheel axle Arm B Page date Page 1 24 01 2011 EASA approved Chapter 06 Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 6 2 1 OWNERS WEIGHT AND BALANCE RECORD Nr Enter all weight change data from aircraft log book in the table below XA42 S N Weight change Operational empty Date Description of Added Removed weight modification Weight Arm Moment Weight Moment kg m kg m Kg kg m Empty weight as O delivered 6 3 CENTER OF GRAVITY CALCULATION SAMPLE 6 3 1 Sample Left main wheel Mmw 294 0 kg Right main wheel Mmw 305 4 kg Tail wheel Min 53 7 kg Empty weight Me Mmw Mmw Mw 653 1 kg Main wheels vertical reference plane A 118 mm Tail wheel vertical reference plane B 4488 mm Center of gravity Empty aircraft XE 477 mm Page 2 Page date Chapter 06 EASA approved 24 01 2011 x gt 6 4 LOADING WEIGHTS AND MOMENTS The maximum number of occupants is 2 Airplane Flight Manual XA42 AFM XA42 0040 002 A 01
39. e piece Lateral loads and twisting moments are conventionally transferred to the fuselage through root ribs combined with a secondary spar and lateral force bolts In front area of the spar there are four tank ribs laminated to the shells which limit the tank capacity of the integral fuel tanks Inspection holes are integrated into the lower wing shell to allow easy inspection of aileron control bell cranks which are mounted on a wing rib The connection to the fuselage is arranged by two bolts through the spar parallel to the center line of the fuselage and two shear force bolts at the secondary spars Ailerons are designed as powered ailerons to reduce pilot s hand forces having a separate airfoil and are hinged at 25 chord They are actuated through pushrods which act on a CFRP arm bolted from the bottom to the aileron This arm extends to 450 mm below the wing and holds so called spades sandwich plates to reduce aerodynamic aileron forces to a minimum The aileron shell is designed as a single cell CFRP sandwich shell which is reinforced by unidirectional CFRP tapes The aileron is hinged in maintenance free teflon bearing bushings mounted on GFRP brackets integrated into the wing connecting ribs To prevent flutter the ailerons are weight balanced in the overhanging leading edge Page 1 Page date Chapter 07 24 01 2011 PT A Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 7 4 EMPENNAGE The aircraft has a cruciform
40. e 7 Chapter 03 ME REDUCE RPM if necessary REDUCE TO 110 kts AVOID higher loads than 1 2 0 8G ASSESS HANDLING LAND ASAP BAIL OUT Page date 24 01 2011 png UT Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 Intentionally left blank Page date Page 8 24 01 2011 Chapter 03 eg gt ai 4 NORMAL PROCEDURES 4 1 GENERAL 4 1 1 AIRSPEEDS FOR NORMAL OPERATION Operation IAS kts IAS km h Climb out after take off 90 160 Cruise climb 90 to 160 160 to 300 Best climb rate V 98 181 Best angle of climb V 78 144 Normal approach 80 150 Approach for short field landing 70 130 4 1 2 CHECKLIST AND PROCEDURES This manual contains the checklist and procedures to operate the aircraft in the utility and the acrobatic category The pilot should be familiar with all procedures contained in the Airplane Flight Manual which must be carried on board The pilot has to comply with checklist for daily check and inspections see chapter 8 4 2 PREFLIGHT INSPECTION 4 2 1 EXTERIOR INSPECTION ILLUSTRATION A Cockpit Canopy B Left rear fuselage C Stabilizer leading edge D Elevator E Vertical stabilizer F Tail wheel G Right rear fuselage H Right wing trailing edge I Right wing leading edge J Right main gear K Right front fuselage L Engine M Propeller N Left front fuselage O Canopy P Left main gear Q Left wing leading edge R Left wing trailing ed
41. ed Utility Acrobatic 1 seat 2 seats Flight Crew Equipment 1 Parachute M M M 3 Seat belt M M 5 Headset M M M O Optional M Mandatory The asterisks used in the above list requires a detailed observation of th e national aviation requirements For airplanes that are registered in the United States the FAR Part 91 General Operating and Flight Rules prescribes each occupant to wear an approved parachute when performing acrobatic maneuvers XtremeAir GmbH highly recommends wearing an approved parachute during all flig Page 11 EASA approved Chapter 02 hts Page date 24 01 2011 Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 Intentionally left blank Page date EASA approved Page 12 24 01 2011 Chapter 02 Airplane Flight Manual XA42 m AFM XA42 0040 002 A 01 3 EMERGENCY PROCEDURES 3 1 INTRODUCTION 3 1 1 GENERAL This section contains the checklist and procedures coping with emergencies that may occur This checklist must be followed in emergencies to ensure maximum safety for the crew and or aircraft The knowledge of these procedures will enable the aircrew to better cope with an emergency The steps should be performed in the listed sequence However the procedures do not restrict the aircrew from taking any additional action necessary to deal with the emergency 3 1 2 GENERAL BEHAVIOR IN EMERGENCY SITUATIONS In any emergency situation contact
42. ed the need for aircraft power ELT qualifications ETSO 2C91a amp ETSO 2C126 EUROCAE ED62 FAA TSO C126 RTCA DO 204 9 1 2 Limitations In europe an ELT is mandatory for bordercrossing flights 9 1 3 Emergency Procedures To send an emergency signal switch the ELT to ON 9 1 4 Normal Procedures There are no changes to POH chapter 4 9 1 5 Performance There are no changes to POH chapter 5 9 1 5 Weight and balance Changes of CG and changes in empty weight are to be considered if the ELT is removed according to chapter 6 of this POH 9 1 7 Description of aircraft and systems Controls 4 2 1 3 1 3 position switch ARM OFF ON 2 Visual indicator red 3 DIN 12 socket for connection to an optional Remote Control Panel a programming dongle or a programming equipment 4 BNC connector for the antenna Features e COSPAS SARSAT Class II 20 C to 55 C e 406 MHz transmission e 121 5 MHz transmission e G Switch sensor compliant with EUROCAE ED62 specifications e Battery KIT BAT200 P N S1840510 01 Page 1 1 Page date Chapter 09 24 01 2011 Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 9 2 TRANSPONDER TRT 800H 9 2 1 GENERAL This supplement contains information for efficient use of the aircraft s transponder The Funkwerk Avionics TRT 800H is installed These informations must be used with the complete manual This supplement is a permanent part of the manual and must be used
43. eded OFF KEEP IDLE OFF PULL CUTOFF OFF OFF Allow engine to cool down at idle for at least 1 min before shutdown Page date 24 01 2011 Page 8 Chapter 04 Airplane Flight Manual XA42 T Ts AFM XA42 0040 002 A 01 4 11 AFTER LEAVING THE AIRCRAFT 4 11 1 SHORT TIME PARKING Nose in the wind TURN Wheels with chocks SECURE 4 11 2 LONG TIME PARKING Fuel selector switch OFF Wheels with chocks SECURE Aircraft at tie down points TIE DOWN Control stick with straps SECURE 4 12 ACROBATIC MANEUVERS 4 12 1 GENERAL Prior to aerobatic flying the aircraft must be carefully checked regarding loose objects For solo flying front cockpit s harness must be secured Solo flying is allowed from the rear seat only The pilot s harness must be as tight as possible Note the maneuver s limitations according to chapter 2 During zero G maneuvers a loss of oil pressure is normal it will stabilise again as any G s are applied The high G forces possible in this aircraft can easily overstress the unaware pilot Each pilot must know his own limits and act careful accordingly Because of the probability concentration of CO gases in the cockpit while performing spins it is strongly recommended to leave the cockpit air vents open all the time Be careful while maneuvering above V 174 kts 322 km h Big and abrupt control inputs with elevator and or rudder can overstress the airframe which can result in catastrophic failure
44. empennage with stabilizers and moveable control surfaces The rudder is balanced aerodynamically at the tip Stabilizer spar consists of PVC foam cores CRP caps and CRP laminates The shell is built using honeycomb sandwich with CRP laminates The control surfaces are built by CRP On the R H elevator half a trim tab is fitted with two hinges The control surfaces are mounted in stainless steel bushings To prevent flutter rudder and elevator are mass balanced The balance weight for the rudder is installed in the rudder tip while the balance weight for the elevator is mounted in the compensating tips 7 5 FLIGHT CONTROL SYSTEM 7 5 1 PRIMARY CONTROL SYSTEM The XA42 is standard equipped with conventional control stick and adjustable rudder pedals The primary control surfaces are operated through direct mechanical linkages 7 5 2 LONGITUDINAL FLIGHT CONTROL SYSTEM The elevator is actuated via a conventional control stick The control movements are from there transferred to the elevator through an idler and 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 airplane is not provided with an inflight controllable aileron trim device 7 5 4 DIRECTIONAL FLIGHT CONTROL SYSTEM The rudder is actuated by control cables Control input is carried from the pilot ped
45. ent markings and placards are provided for the acrobatic category only for utility category refer to corresponding limitations This aircraft is certified under Type Certification Data Sheet EASA A 507 Any exceedance of given limitations has to be reported by the pilot so that necessary inspection or maintenance procedures according to the maintenance manual can be performed 2 2 AIRSPEED IAS Never exceed speed Vne 225 kts Maximum structural cruising speed Vno 185 kts Maneuvering speed Va 174 kts Maximum operating maneuvering speed Vo 174 KIAS 2 3 CROSSWIND COMPONENT The maximum demonstrated crosswind component for take off and landing is 25 kts 47 km h 2 4 ENGINE Engine type is Lycoming AEIO 580 B1A with a rated power of 235 kW 315 hp 2700 rpm 2 4 1 FUEL Minimum grade aviation gasoline 100LL for alternate fuel grades see latest revisions of Lycoming S I No 1070P Total fuel capacity 275 1 72 5 US gal Usable fuel capacity 273 72 0 US gal Page 1 EASA approved Page date Chapter 02 24 01 2011 Airplane Flight Manual XA42 T Ts AFM XA42 0040 002 A 01 For acrobatic flights the wing tanks must be empty Total fuel capacity Acro 651 17 1 US gal Usable fuel capacity Acro 64 16 9 US gal 2 4 2 ENGINE LIMITATIONS RPM e Max takeoff Acrobatic 2700 rpm Utility 2670 rpm e Max continuous 2500 rpm Oil temperature e Normal operation 38 117 C 100 245 F e Maximum 118 C 245 F Oil
46. es an entry speed of at least 100 kts 185 km h Gyroscopic manoeuvers All maneuvers with high rates of rotation in the pitch and yaw axis cause high stress to the crankshaft There is no RPM limitation for gyroscopic maneuvers Be aware of the risk of a higher engine wear during gyroscopic maneuvers Page date Page 10 24 01 2011 Chapter 04 Airplane Flight Manual XA42 T Ts AFM XA42 0040 002 A 01 4 12 3 SPIN Spin entry Airspeed REDUCE At reaching stall speed Rudder to desired direction of spin APPLY Aileron NEUTRAL Elevator PULL The aircraft falls in a stable spin The loss of altitude for 6 turns of standard spin rudder deflected aileron neutral elevator pulled power off is about 2300 ft Applying aileron against the direction of spin will cause a flat spin aileron into the direction of spin will cause a spiral dive Applying aileron into the direction of spin will cause a flat spin aileron against the direction of spin will cause a Spiral dive To induce inverted spins the elevator must be pushed and aileron action is reversed Spin recovery Rudder against direction of spin APPLY Throttle IDLE Ailerons NEUTRAL Elevator NEUTRAL The spin stops within a half revolution Recovery is accelerated by aileron deflection into the direction of rotation Recovery can be severely handicapped or completely blocked by aileron against rotation If loss of orientation occurs during spin Throttle IDLE Hard
47. ff run over 50 ft obstacle 6000 Take off run over 50 ft obstacle Take off run 7000 EOS over 50 ft obstacle 8000 Take off run over 50 ft obstacle Page date Page 4 24 01 2011 Chapter 05 Airplane Flight Manual XA42 T Ts AFM XA42 0040 002 A 01 5 5 2 TAKE OFF DISTANCES FOR ACROBATIC CATEGORY TAKE OFF WEIGHT Conditions mMrow 850 kg Lift off speed 70 KIAS 130 km h Speed over 50 ft obstacle Vso 80 KIAS 150 km h Power setting full throttle 2700 rpm Pressure altitude Temperature C ft Ed S S 0 S 0 SA 30 0 SL a estra 1000 u 2000 EIeI6CIIXGIN 3000 ao peme 4000 oo p 6000 EG 7000 5000 over 50 ft obstacle 8000 over 50 ft obstacle 425 463 Page 5 Page date Chapter 05 24 01 2011 Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 ER 5 6 RATE OF CLIMB PERFORMANCE Speed for best rate of climb Vy 90 kts 167 km h Speed for best angle of climb Vx 78 kts 145 km h Climb rate in ft min for best rate of climb best angle of climb Utility flight mrow 999 kg 2720 2456 Acrobatic flight mrow 850 kg 3266 3000 5 7 CRUISE PERFORMANCE RANGE ENDURANCE AND FUEL CONSUMPTION In the range included is a 60 min reserve at the determined power setting starting with full fuel of 275 L 72 5 US gal Economy mix Best power mix Limit 75 Press Alt OAT ISA RPM MP TAS Endurance Range
48. ft obstacle 48 s Landing run 0 3000 over 50 ft obstacle 503 5 F Landing run 5000 over 50 ft obstacle Landing run 6000 over 50 ft obstacle Pu Landing run 7000 over 50 ft obstacle ISA 10 ISA 20 ISA 30 F Landing run 4000 over 50 ft obstacle m Landing run 8000 over 50 ft obstacle Page date Page 8 24 01 2011 Chapter 05 png 5 Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 Intentionally left blank Page 9 Page date Chapter 05 16 03 2010 ha on 6 WEIGHT amp BALANCE AND EQUIPMENT LIST 6 1 GENERAL This section describes the procedure for establishing the basic weight and moment of the aircraft Sample forms are provided for reference Procedures for calculating the weight and movement for various operations are also provided A comprehensive list of all equipment available for this aircraft is It is the responsibility of the pilot to ensure that the aircraft is loaded within the limits 6 2 AIRCRAFT WEIGHING PROCEDURE A Drain all fuel tanks to non usable fuel level B Position scales capable of min 300 kg each under each wheel C Support tail wheel until water level firewall vertical shows aircraft in level attitude D Read each scales reading subtract support s weight if necessary Determination of the momentum arms A The firewall is vertical reference plane use plumb bob to mark plane on the ground B By using a plumb bob draw a line from middle of right wheel axle to middle of left axl
49. ge 4 2 2 GENERAL Visually check airplane for general condition during walk around inspection Perform exterior check as outlined in the picture above in counter clockwise direction Page 1 Page date Chapter 04 24 01 2011 Airplane Flight Manual XA42 png A AFM XA42 0040 002 A 01 4 3 CHECKLIST PROCEDURES A Cockpit Canopy AFM and legal documents CHECK ON BOARD Ignition Master switch OFF Clear of foreign objects CHECK Baggage compartment CHECK Front seat harness SECURED Controls free movement CHECK Throttle free movement CHECK Master switch ON Fuel capacity indication CHECK Master switch OFF Canopy frame and glass to damage CHECK B Left rear fuselage Fuselage skin to damage CHECK Static port clean CHECK Smoke tank vent overflow port clean CHECK C Stabilizer leading edge Stabilizer leading edge and skin to damage CHECK D Elevator Elevator trailing edge and skin to damage CHECK Elevator hinges CHECK Elevator linkage CHECK Elevator for free movement and play CHECK Servotab for damage hinges and free movement CHECK E Vertical stabilizer Vertical stabilizer leading edge and skin for damage CHECK Rudder trailing edge and skin for damage CHECK Rudder hinges CHECK Rudder linkage CHECK Rudder for free movement and play CHECK F Tail wheel General condition of strut CHECK Freedom of movement and play CHECK Page date Page 2 24 01 2011 Chapter 04 Airplane Flight Manual XA42 AFM XA42 004
50. ility flights all the tanks may be used During acrobatic flights the wing tanks must be empty The total volume of all three tanks is 275 L 72 5 US gal The acro tank which must be used for take off landing and acrobatics has a capacity of 65 L 17 1 US gal The fuel selector valve is labeled ACRO accordingly Fuel is picked up through a flop tube from an 11 L 2 9 US gal header tank located underneath the acro tank This header tank s capacity adds to the acro tank meaning the usable fuel is in fact 76 L 20 0 US gal but due to the fact that the fuel probe does no extend in the header tank the header tank is excluded from the fuel capacity indication and therefore also flights must be planned without these 11 L 2 9 US gal The header tank is gravity fed by the acro tank via a 3 4 tube During inverted flight the header tank is not refilled which limits the time of inverted flight to the use of 11 L app 3 min at full power In case the inverted flight is extended too long and the engine quits it takes app 10 sec to refill the header tank enough for the engine to restart Therefore it is recommended not to perform inverted flight for more than 2 min uninterruptedly Due to the flop tube in the header tank the acro tank can be flown down to 0 5 L even at high yaw and bank angles The acro tank is mounted in and supported by the tank compartment of the fuselage The two wing tanks are located in the inner 3 compartments wing root
51. l are about 30 recovery can be achieved without altitude loss Power off stalls are announced by slight shuddering of the aircraft 5 kts above the stall Pitchdown and roll are about 30 altitude loss for recovery about 100 ft Stallspeeds IAS Bank angle laod factor 0 1 15 1 04 Utility 999 kg KIAS Aeobatic 850 kg KIAS 57 52 53 1 15 56 Page 3 Chapter 05 Page date 24 01 2011 T ML Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 5 5 TAKE OFF PERFORMANCE The mentioned take off distances are valid for a hard surface runway clean aircraft and no wind For other conditions use following factors Wind 10 kts headwind distances are reduced by 15 20 kts headwind distances are reduced by 30 for each 3 kts tailwind distances are increased by 10 Runway Distances on a dry hard grass runway are 10 longer For wet soft and uneven fields factors must be determined individually by the PIC 5 5 1 TAKE OFF DISTANCES FOR UTILITY CATEGORY TAKE OFF WEIGHT Conditions mMrow 999 kg Lift off speed 70 KIAS 130 km h Speed over 50 ft obstacle Vso 80 KIAS 150 km h Power setting full throttle 2670 rpm Pressure altitude Distance Temperature C ft m ISA ISA 10 ISA 20 ISA 30 run over 50 ft obstacle EW run over 50 ft obstacle am feat run over 50 ft obstacle sooo paeet run over 50 ft obstacle oon mies run over 50 ft obstacle 5000 Take o
52. lying from the rear seat only The maximum is 2 persons in both categories where the pilot in command is seated in the rear seat and the front seat occupant passenger is seated in the front seat It is required to use a headset 2 12 KINDS OF OPERATIONAL LIMITS Flying is allowed under VFR day conditions only Flight under icing conditions is prohibited Smoking is prohibited Areas where the risk of lightning exist should be avoided The aircraft may be operated at OAT from 20 C 4 F to 38 C 100 F 2 13 STRUCTURAL TEMPERATURE COLOR LIMITATION The structure is qualified up to 72 C 161 F Flying with structural temperature above 72 C 161 F is prohibited To avoid high temperatures paint colours have to comply with XtremeAir s color specification for composite structure 2 14 MAXIMUM OPERATING ALTITUDE The certified maximum operating altitude is 15 000 ft 4572 m MSL 2 15 TYRE PRESSURE The tyre pressure for the main landing gear is 3 0 bar 43 5 psi The tail wheel is solid rubber 2 16 SMOKE OIL Straight paraffin oil viscosity 30 50 cts at 20 C 68 F initial boiling point gt 330 C 626 F For example Fauth FCO5 Texaco Canopus 13 or equivalent 2 17 MARKINGS AND PLACARDS 2 17 1 AIRCRAFT IDENTITY PLACARD oe 9 MANUFACTUREF Vipa Air mala R XtremeAir GmbH MODEL XA42 ERIAL NUMBER REGISTRATION O Page date EASA approved Page 6 2
53. nding gear is equipped with hydraulic disc brakes 7 8 SEAT AND SEATBELTS The seat has an economically shaped glass carbon reinforced structure The rudder pedal s position is adjustable Seatbelts consist of two shoulder straps two left and two right lap belts and a crotch strap All belts are adjustable and the lap belt has a stainless steel ratchet tightener During all acrobatic maneuvers the seat belts must be as tight as possible Page 5 Page date Chapter 07 09 11 2010 png ean EU Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 7 9 CANOPY The canopy is one single part that is hinged on the right hand side via 3 integral hinges equipped with brass bushings to the fuselage and locked on the left hand side of the aircraft The lock is redundant as there are three bolts moving in opposite directions The canopy can be opened manually by pulling the interior or exterior lever and lifting it up to the right hand side A strap in the back of the canopy will prohibit its opening range To securely close and lock the canopy pull the lever and let the canopy slip over the latch In case of emergency the operation is equal to the procedures above Due to the shape of the canopy there is a lower pressure on the upper side that will immediately open the canopy after it is unlocked 7 10 POWER PLANT 7 10 1 ENGINE The power plant is a Lycoming AEIO 580 B1A with a rated maximum take off power of 235 kW 315 hp 2700 rpm It is a
54. out the XtremeAir GmbH EASA approval The editor has the copyright of this Airplane 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 XtremeAir GmbH coming along with the Airworthiness Directive AD publication issued by the EASA The owner is responsible for incorporating prescribed amendments and should make notes about these on the records of amendments Should this Airplane Flight Manual get lost please inform XtremeAir GmbH HarzstraBe 2 Am Flughafen Cochstedt 39444 Hecklingen Germany Should this Airplane Flight Manual be found kindly forward it to the civil aviation authority in the country the aircraft is registered Page date Page VI 24 01 2011 Airplane Flight Manual XA42 png an ET UE AFM XA42 0040 002 A 01 WARNINGS CAUTIONS AND NOTES The following definitions apply to Warnings Cautions and Notes Operating procedures techniques etc which could result in personal injury or loss of life if not carefully followed Operating procedures techniques etc which could result in damage to equipment Operating procedures techniques etc which are considered essential to emphasize if not carefully followed Page VII Page date 24 01 2011 PT A Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 Intentionally left blank Page
55. pacitive operated indicator To verify the fuel indication in the tanks the use of dipstick XA 2840 230 is highly recommended Page date Page 8 24 01 2011 Chapter 07 Airplane Flight Manual XA42 PT A AFM XA42 0040 002 A 01 7 11 2 FUEL SELECTOR VALVE The fuel selector can be operated from the rear cockpit pilot There is no access from the front cockpit front seat occupant guest The fuel selector valve is mounted below the main tank and behind the firewall A linkage with universal joints connects the selector lever and the valve To select the tank in use Lift the knob and turn the handle 90 LEFT RIGHT or 180 ACRO so that the red knob points towards the tank in use To turn off the fuel supply lift the knob and turn it until it faces downwards OFF KNOB Fig 7 11 2 Fuel Selector 7 12 ELECTRICAL SYSTEM The electrical system is a 12 Volt direct current system Power is supplied by a gear driven alternator 13 75 V DC 20 A with regulator field is switched via alternator switch which feeds the onboard battery 12 V 18 Ah In case of emergency the battery will supply all direct current loads with power for 30 minutes The electrical system is controlled by means of switches which are arranged on the righthand electronic panels The instruments are secured via individual circuit breakers on the righthand electronic panel The system contains the master switch relay and the starter with own rel
56. peeds in this chapter are indicated air speeds IAS except otherwise stated The performance figures below are given under following conditions e Maximum allowed weight 999 kg 2200 lbs except otherwise stated e Take off and landing on concrete surface e No wind e Standard atmospheric condition 5 1 2 DEFINITION OF TERMS For definition of terms abbreviations and symbols refer to chapter 1 Page 1 Page date Chapter 05 24 01 2011 ET UT Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 5 2 ISA CONVERSION ISA Conversion of pressure altitude and outside air temperature are shown in the following figure Temperature F 80 15 14 13 de A O e N Lu o Pressure Altitude PA ft 1000 00 oa 0 Temperature C Page date Page 2 24 01 2011 Chapter 05 Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 peme 5 3 AIRSPEED CALIBRATION 220 200 180 160 1 1 T T I 1 1 1 T 140 IAS kt 120 l i p A 100 L i I 80 L I 60 L I I I I I I 40 40 60 80 100 120 140 160 180 200 220 CAS kt Indicated airspeed assumes zero instrument error 5 4 STALL SPEED Below 60 kts IAS the control s sensibility decreases and the stall is announced by a slight shudder 6 kts before stalling While executing power on stalls the aircraft starts to wiggle around the pitch and roll axis Deck angle is around 70 to 80 Pitchdown and rol
57. qt Minimum sump quantity 8 52 L 9 qt For oil temperatures and oil grades refer to chapter 1 7 10 3 ENGINE INSTALLATION The engine is attached to the steel tube engine mount using 4 shock mounts The engine mount itself is connected to the fuselage with 14 bolts on the firewall surface The cowling is separated in a lower and an upper part both are carbon fiber glass fiber reinforced composites The upper cowling houses a hatch to easily check the oil dipstick 7 10 4 PROPELLER The aircraft is equipped with a constant speed 3 blade MTV 9 B C C203 20d propeller The diameter is 2030 mm It is produced by MT Propeller Entwicklungs GmbH blades are made out of wood and composite 7 10 5 THROTTLE Parallel motion control mounted on the left side of both cockpits 7 10 6 MIXTURE Vernier control located at the left side of the rear cockpit red knob 7 10 7 RPM CONTROL Vernier control on the left side of the rear cockpit blue knob Preselection of RPM possible due to constant speed governor 7 10 8 EXHAUST SYSTEMS The aircraft is equipped with an exhaust system that merges three pipes on each side of the engine into one tail pipe on each side These two tail pipes exit the cowling through special outlets Page 7 Page date Chapter 07 09 11 2010 T Ts Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 7 11 FUEL SYSTEM 7 11 1 GENERAL The fuel system consists of two separate wing tanks and one acro tank For ut
58. r 03 Page 1 A 01 Chapter 03 Page 2 and Chapter 03 Page 3 A 01 Chapter 03 Page 4 and Chapter 03 Page 5 A 01 Chapter 03 Page 6 and Chapter 03 Page 7 A 01 Chapter 03 Page 8 and Chapter 04 Page 1 A 01 Chapter 04 Page 2 and Chapter 04 Page 3 A 01 Chapter 04 Page 4 and Chapter 04 Page 5 A 01 Chapter 04 Page 6 and Chapter 04 Page 7 A 01 Chapter 04 Page 8 and Chapter 04 Page 9 A 01 Chapter 04 Page 10 and Chapter 04 Page 11 A 01 Chapter 04 Page 12 and Chapter 05 Page 1 A 01 Chapter 05 Page 2 and Chapter 05 Page 3 A 01 Chapter 05 Page 4 and Chapter 05 Page 5 A 01 Chapter 05 Page 6 and Chapter 05 Page 7 A 01 Chapter 05 Page 8 and Chapter 05 Page 9 A 01 Chapter 06 Page 1 and Chapter 05 Page 2 A 01 Chapter 06 Page 3 and Chapter 06 Page 4 A 01 Chapter 06 Page 5 and Chapter 06 Page 6 A 01 Chapter 06 Page 7 and Chapter 07 Page 1 A 01 Chapter 07 Page 2 and Chapter 07 Page 3 A 01 Chapter 07 Page 4 and Chapter 07 Page 5 A 01 Chapter 07 Page 6 and Chapter 07 Page 7 A 01 Chapter 07 Page 8 and Chapter 07 Page 9 A 01 Chapter 07 Page 10 and Chapter 07 Page 11 A 01 Chapter 08 Page 1 and Chapter 08 Page 2 A 01 Chapter 08 Page 3 A 01 Page ate Page II 24 01 2011 Airplane Flight Manual XA42 pn TUT AFM XA42 0040 002 A 01 TABLE OF CONTENTS LOG OF REVISIONS U U U U U U U u u u u u u II LOG OF EFFECTIVE PAGES tee III TABEL OF CONTENTS TN IV INTRODUCTION ERRF
59. re and wheel slip mark Q Left wing leading edge Wing leading edge and skin for damage Fuel cap and fuel capacity Left wing tank Pitot tube for choking and damage R Left wing trailing edge Spade and spade arm Aileron linkage Wing trailing edge and skin for damage Aileron trailing leading edge and skin for damage Aileron hinges Freedom of movement and play Page date 24 01 2011 CHECK CHECK CHECK CHECK CLOSE CHECK CHECK CHECK CHECK CHECK CHECK CHECK CHECK CHECK CHECK DRAIN CHECK CHECK CHECK CHECK CHECK CHECK CHECK ME Page 4 Chapter 04 Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 4 4 STARTING PROCEDURES Startup Canopy Straps Fuel selector switch to ACRO tank Avionic switch OFF Master switch Propeller control Mixture Throttle Electric fuel pump Throttle Mixture Elevator Brake Propeller area FREE Starter When engine starts to fire 1000 rpm with throttle Oil pressure Avionic switch Warm up 2 min 1000 rpm Afterwards 1500 rpm Until oil temperature reaches 100 F 4 5 TAXIING THE AIRCRAFT Brakes Elevator pulled Page 5 Chapter 04 ME CLOSED and LOCKED ATTACH and TIGHTEN SWITCH CHECK ON PUSH FINE PITCH PUSH FULL RICH FULL OPEN ON 3 sec IDLE PUSH 3mm OPEN CUT OFF PULL APPLY CHECK and CALL ENGAGE FEED IN MIXTURE ADJUST CHECK must rise within 30 sec ON CHECK ADJUST CHECK RELEASE KEEP Page date
60. rformed by the manufacturer exclusively Intention is to protect the aircraft s airworthiness state Informations regarding repairs are contained in the maintenance manual 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 the chapter 2 and 7 Page date Page 1 24 01 2011 Chapter 08 Airplane Flight Manual XA42 png mE AFM XA42 0040 002 A 01 8 6 GROUND HANDLING a Due to its low weight and the free swiveling tail wheel two persons can easily move the airplane by hand The best spot to push is the leading edge of the wings the best spot to pull is the propeller close to the root of the blades b If the aircraft is parked in the open secure the wheels with chocks When windy tie down the aircraft For this purpose use ropes to tie down the tail wheel and each wing at the outer aileron hinges The control stick can be set fix with the seatbelt If the aircraft is parked outdoors it must be protected against the effects of weather the degree of protection depending on severity of the weather conditions and the expected duration of the parking period When the airplane is parked in good weather conditions for less than a half day park the aircraft headed into the wind and place wheel chocks at the main wheels c To level the aircraft the tail wheel is rested on a balance and jacked to a position that the fuselage reference line firew
61. rudder pedal APPLY Stick CENTER The spin stops within 1 turn and the aircraft can be recovered from the resulting dive Page 11 Page date Chapter 04 24 01 2011 Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 Intentionally left blank Page date Page 12 24 01 2011 Chapter 04 Airplane Flight Manual XA42 png ET UT AFM XA42 0040 002 A 01 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 60 minutes reserve fuel at specified speeds Some indeterminate variables such as engine and propeller air turbulence and others may account for variations as high as 10 or more in range and endurance Therefore it is important to utilize all available information to estimate the fuel required for the particular flight 5 1 1 PERFORMANCE CHARTS Performance data are presented in tabular or graphical form to illustrate the effect of different variables Sufficiently detailed informations are provided in the tables so that conservative values can be selected and used to determine the particular performance figure with reasonable accuracy All s
62. s After power ON the display shows the name of the instrument and the software version as shown in Fig 9 2 7 2 TRT SOOH w 2 51 FPGA Vers 21 Fig 9 2 7 2 power ON display Operations Transponder Mode Selection Press MOD repeatedly to select from the following modes e ACS Standard condition transponder responds to mode A C and S interrogations e A S Altitude is not transmitted neither on C nor on S requests Other S data are transmitted e STBY Transponder only responds to directly addressed Mode S interrogations squitter remains active If a ground switch is connected actuation of this switch will cause the transponder switch to STBY Operations Squawk Setting Turn the knob to adjust the numbers push the horizontal arrow to step from digit to digit of the stand by Squawk Codes lower line Push the vertical arrow to swap stand by and active squawk Page 2 2 Page date Chapter 09 24 01 2011
63. seeseuesauesansnnaets 1 06 6 3 CENTER OF GRAVITY CALCULATION SAMPLE cocccccccconnncoconnnnnnonononconcnnnnnnnnoranaarennnnnns 2 06 6 4 LOADING WEIGHTS AND MOMENTS cocccocccnnccncccnncnnnonanonnccnnonaronaronaroncororrnnnrnnnrnnncnanes 3 06 6 5 WEIGHTS AND MOMENTS LIMIT S cccoccconicnncnnaconncnnnonaconncnnnnnnronoronarencronrronaronnenannnnnos 4 06 6 6 EUIPMENT LIST XA42 S N lOl coonconnccconnncnnnnnconcoconanononrronnrnnnaroronarnnanrronarrn narra kawanqa 5 06 7 DESCRIPTION AND OPERATION OF AIRCRAFT AND SYSTEMS 1 07 Zils AIRCRAFT essen rennen aid 1 07 12 FUSELAGE sia 1 07 7 3 WING baina dada 1 07 7 4 EMPENNAGE insista 2 07 7 5 FLIGHT CONTROL SYSTEM u uu u ul anna a 2 07 7 6 INSTRUMENTATION 0c eccceccseesceeseeeesseeueecueeeueeesenseensesuseseeeseueseueeaeeeeesegseagesauesagees 3 07 7 7 LANDING GEAR Z uyu unun arnaca Sa AE rial denn anna anne 5 07 7 8 SEAT AND SEATBELTS isaac ea ran 5 07 79 CANOPY otitis 6 07 7 10 POWER PLAN Tacos aan 6 07 7 11 FUEL SYSTEM vostra ana 8 07 7 12 ELECTRICAL SYSTEM u aa aaa 9 07 7 13 CABIN ENVIRONMENT CONTROL a nnnn nennen nennen nennen nnn nennen 9 07 7 14 BAGGAGE COMPARTMENT zusesssennnnnnnnnnnnnnn nn nun nun nen nun nun nennen nennen nun nn nnnn nun ennn nen 10 07 7 15 PITOT ST TIESYSTEM coso 10 07 2 16 SMOKESYSTEM iz s im uu 020000508 daran AA a a terre 10 07 8 HANDLING SERVICING AND MAINTENANCE
64. shed reduces the glide ratio to E 5 5 Loss of oil pressure puts the prop to coarse pitch using the prop for glide ratio control is not possible when oil pressure is lost Suitable terrain SELECT Fuel selector switch OFF Mixture CUTOFF CHECK Master switch OFF CHECK Straps TIGHTEN Page date Page 4 24 01 2011 Chapter 03 Airplane Flight Manual XA42 png 5 AFM XA42 0040 002 A 01 Final and landing Approach speed 80 KIAS 150 km h Glide angle with speed CONTROL After touchdown APPLY BRAKES 3 4 2 PRECAUTIONARY LANDING WITH ENGINE POWER Proceed like short field landing additionally in short final MASTER SWITCH OFF 3 5 FIRES 3 5 1 DURING START ON GROUND Fuel selector switch OFF Throttle FULL OPEN Mixture PULL CUTOFF Master switch OFF After engine failure Ignition OFF Aircraft LEAVE IMMEDIATELY Fire extinguishing point fire extinguisher towards air inlets Do not remove cowling while fire alight 3 5 2 ENGINE FIRE IN FLIGHT Fuel selector switch OFF Throttle FULL OPEN Mixture PULL CUTOFF Master switch OFF After engine failure Ignition OFF Glide and emergency dead stick landing EXECUTE If fire does not stop and landing is not practical after 5 minutes BAIL OUT 3 6 ICING INADVERTENT ENCOUNTER In the case of an icing encounter turn back or change altitude to obtain an outside temperature that is less conductive to icing In advance plan a landing at the nearest airfield With extremely rapid
65. should be established with a ground station as soon as possible after completing the initial corrective action Include position altitude heading speed nature of the emergency and pilot s intentions in the first transmission There after the ground station should be kept informed of the progress of the flight and of any changes or developments in the emergency Three basic rules apply to most emergencies and should be observed by the pilot 1 Maintain aircraft control 2 Analyze the situation and initiate 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 judgment the flight may be safely continued to an airfield where more adequate facilities are available Make only one attempt to restore an automatically disconnected power source or reset or replace an automatically disconnected circuit breaker that affects flight operations or safety Each repetitive attempt to restore an automatically disconnected power source or the resetting of an automatically disconnected circuit breaker can result in progressively worse effects Page 1 Page
66. 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 see type placard c A maintenance manual with revision service may be procured from the manufacturer 8 2 AIRPLANE INSPECTION PERIODS As required by national operating rules all airplanes must pass a complete annual inspection every twelve calendar months In addition to the annual inspection airplanes must pass a complete inspection after every 100 flights hours with a minor check after 50 hours The airworthiness authority may require other inspections by the issuance of airworthiness directives applicable to the aircraft engine propeller and components The owner is responsible for compliance with all applicable airworthiness directives and periodical inspections 8 3 PILOT CONDUCTED PREVENTIVE MAINTENANCE Pilots operating the airplane should refer to the regulations of the country of certification for information of preventive maintenance that may be performed by pilots All other maintenance required on the airplane is to be accomplished by appropriately licensed personnel A licensed maintenance company should be contacted for further information Preventive maintenance should be accomplished with the appropriate service manual 8 4 CHANGES OR REPAIRS Only licensed personnel is permitted to accomplish changes or repairs Changes to the aircraft must be pe
67. ual XA42 AFM XA42 0040 002 A 01 6 6 EQUIPMENT LIST XA42 S N Part or P N Weight Arm Required R Qty Item Manufacturer kg m Optional 0 1 Engine Lycoming Engines AEIO 580 B1A 202 30 0 61 R 1 Magneto LH Slick 6350 2 00 0 15 R 1 Magneto RH Slick 6393 2 30 0 15 R 1 Slick Start Unison SS1001 0 27 0 02 R 4 Shock Mount Lord J 7764 20 0 43 0 29 R 1 Alternator B amp C SD20 4 40 0 15 R 1 Voltage Regulator B amp C LR3C 14 0 25 0 3 R 1 Starter B amp C BC315 100 2 4 70 0 90 R 1 Fuel Injector Bendix RSA 10AD1 3 90 0 69 R 1 Aux Fuel Pump Weldon Pump 8120 G 1 10 0 41 R 2 Oil Cooler Setrab 50 113 7612 0 50 0 07 R 1 Fuel Oil and Sensor Hose Set Welbhoff div 4 20 0 25 R 1 Exhaust System LH Gomolzig XA42 7810 151 3 90 0 61 R 1 Exhaust System RH Gomolzig XA42 7810 156 3 90 0 61 R 1 Propeller Vernier Control ACS Products A 790 101 0 61 0 86 R 1 Mixture Vernier Control ACS Products A 970 113 5 0 65 0 98 R 1 Throttle Control ACS Products A 920 67 5 0 50 0 65 R 1 Propeller MT Propeller MTV 9 B C C203 30 50 1 22 R 1 Spinner MT Propeller 20d 0 80 1 35 R 1 Governor MT Propeller P 880 5 1 30 0 95 R 1 Cowling bottom XtremeAir GmbH XA42 7110 150 5 80 0 65 R 1 Cowling top XtremeAir GmbH XA42 7110 152 3 60 0 65 R 1 Canopy XtremeAir GmbH XA42 5210 050 13 10 1 50 R 1 Main Tank Assy XtremeAir GmbH XA42 2810 050 5 1
68. which is unique to the particular aircraft Mode A replies consisting of any one of 4 096 codes Squawk which differ in the position and number of pulses Mode C replies including encoded flight level Mode S replies including aircraft address and flight level Acquisition Squitter including aircraft address and flight level Extended Squitter additionally including position and velocity IDENT capability for activating the Special Position Identification SPI pulse for 18 s Page date Page 2 1 04 12 2009 Chapter 09 Airplane Flight Manual XA42 pnp ean ET Uy AFM XA42 0040 002 A 01 certified to EUROCAE ED 73B and CS ETSO 2C1 1 2a maximum flight level 35000 ft maximum velocity 250 knots Display information contains code reply symbol mode of operation and pressure altitude temperature compensated high precision piezo resistive pressure sensor RS 232 I O data port 8 entries for AA AC Code FID Ground Switch GPS Interfacesetting Operations Table of functions ON OFF ON press for 0 5 s OFF press for 3 s activate VFR also deactivate VFR select VERD VFRW store active squawk as VFR VFRW squawk swap active and stand by squawk IDENT activate SPI pulse MODE select mode ACS A S or stand by FID select FID setting in stand by mode press for 5 s X X X X set according squawk digit X set cursor when entering AA AC FID X change values select option

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