XtremeAIR XA42 Flight Manual Download

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Airplane Flight Manual XA42
AFM-XA42-0040-002-A.01

Page

Page date :

Chapter 04

24.01.2011

4.4

STARTING PROCEDURES

Startup:

Canopy

CLOSED and LOCKED

Straps

ATTACH and TIGHTEN

Fuel selector switch to ACRO tank

SWITCH

Avionic switch OFF

CHECK

Master switch

Propeller control

PUSH FINE PITCH

Mixture

PUSH FULL RICH

Throttle

FULL OPEN

Electric fuel pump

ON 3 sec.

Throttle

IDLE, PUSH 3mm OPEN

Mixture

CUT-OFF

Elevator

PULL

Brake

APPLY

Propeller area FREE

CHECK and CALL

Starter

ENGAGE

When engine starts to fire

FEED IN MIXTURE

1000 rpm with throttle

ADJUST

Oil pressure

CHECK (must rise within 30 sec.)

Avionic switch

Warm-up:

2 min 1000 rpm

CHECK

Afterwards 1500 rpm

ADJUST

Until oil temperature reaches 100 °F

CHECK

4.5

TAXIING THE AIRCRAFT

Brakes

RELEASE

Elevator pulled

KEEP

Summary of Contents for XA42

Page 1: ...aße 2 Am Flughafen Cochstedt 39444 Hecklingen Germany 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 ...

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Page 3: ...Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 Page I Page date 24 01 2011 Intentionally left blank ...

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Page 5: ...Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 Page date Page II 24 01 2011 LOG OF REVISIONS Issue Date Approved A 01 27 01 2011 ...

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Page 7: ... Chapter 04 Page 4 and Chapter 04 Page 5 Chapter 04 Page 6 and Chapter 04 Page 7 Chapter 04 Page 8 and Chapter 04 Page 9 Chapter 04 Page 10 and Chapter 04 Page 11 Chapter 04 Page 12 and Chapter 05 Page 1 Chapter 05 Page 2 and Chapter 05 Page 3 Chapter 05 Page 4 and Chapter 05 Page 5 Chapter 05 Page 6 and Chapter 05 Page 7 Chapter 05 Page 8 and Chapter 05 Page 9 Chapter 06 Page 1 and Chapter 05 Pag...

Page 8: ...E 2 02 2 5 PROPELLER 3 02 2 6 WEIGHT LIMITS 3 02 2 7 WEIGHT AND CENTER OF GRAVITY ENVELOPE 3 02 2 8 BAGGAGE 3 02 2 9 ACROBATIC MANEUVERS 4 02 2 10 LOAD FACTORS 5 02 2 11 FLIGHT CREW LIMITS 6 02 2 12 KINDS OF OPERATIONAL LIMITS 6 02 2 13 MAXIMUM OPERATING ALTITUDE 6 02 2 14 TYRE PRESSURE 6 02 2 15 SMOKE OIL 6 02 2 16 MARKINGS AND PLACARDS 6 02 2 17 KINDS OF OPERATION EQUIPMENT LIST 10 02 3 EMERGENC...

Page 9: ...NG PROCEDURE 1 06 6 3 CENTER OF GRAVITY CALCULATION SAMPLE 2 06 6 4 LOADING WEIGHTS AND MOMENTS 3 06 6 5 WEIGHTS AND MOMENTS LIMITS 4 06 6 6 EUIPMENT LIST XA42 S N 101 5 06 7 DESCRIPTION AND OPERATION OF AIRCRAFT AND SYSTEMS 1 07 7 1 AIRCRAFT 1 07 7 2 FUSELAGE 1 07 7 3 WING 1 07 7 4 EMPENNAGE 2 07 7 5 FLIGHT CONTROL SYSTEM 2 07 7 6 INSTRUMENTATION 3 07 7 7 LANDING GEAR 5 07 7 8 SEAT AND SEATBELTS ...

Page 10: ...l must not be exchanged and no alterations of or additions to the approved contents may be made without 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 manufac...

Page 11: ...arnings 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 if not carefully followed Operating procedures techniques etc which are considered essential to emphasize WARNING CAUTION NOTE ...

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Page 13: ...Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 Page date Page VIII 24 01 2011 Intentionally left blank ...

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Page 15: ...formance 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 Harzstraße 2 Am Flughafen Cochstedt 39444 Hecklingen Germany ...

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Page 17: ...Airplane Flight Manual XA42 AFM XA42 0040 002 A 01 Page date Page 2 24 01 2011 Chapter 01 1 4 TECHNICAL DATA 1 4 1 3 VIEW DRAWING All dimensions in millimeters ...

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Page 19: ...ng 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 40...

Page 20: ... Utility 233 kW 312 hp 2670 rpm 1 6 PROPELLER Manufacturer MT Propeller Entwicklung GmbH 94348 Atting Germany Type MTV 9 B C C203 20d 1 7 EXHAUST SYSTEM Manufacturer Gomolzig GmbH Eisenwerkstraße 9 58332 Schwelm Germany Type 3 in 1 each side 1 8 FUEL Fuel type Aviation Gasoline Avgas 100LL For alternative fuel grades see latest issue of Textron Lycoming S I No 1070 Minimum Maximum 100 130 octane T...

Page 21: ... Oil type Straight paraffin oil viscosity 30 50 cts at 20 C 68 F initial boiling point 330 C 626 F For example Fauth FC05 Texaco Canopus 13 or equivalent Total Smoke Oil capacity 28 l 7 4 US gal 1 11 LOADING Utility Category Acrobatic Category Wing Loading kg m 2 84 4 75 5 Power Weight Ratio kg hp 1 3 01 2 69 1 12 TERMINOLOGY Air Speeds CAS Calibrated air speed CAS TAS in standard atmospheric cond...

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Page 23: ...US gal 3 79 Liter US quartt US liquid quart 1 US qt 0 946 Liter hp Horse power English h Hour kts Knots nautical miles per hour km h Kilometer per hour lbs English pound 1 lbs 0 4536 kg MP Manifold pressure NM Nautical mile 1 nm 1 852 km rpm Revolutions per minute CG Center of gravity Arm Is the horizontal distance from reference datum Moment Is the product of the weight of an item multiplied by i...

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Page 25: ...2 170 315 170 92 135 250 260 140 9000 2743 2375 7792 180 333 180 97 140 259 270 146 9500 2896 2500 8202 190 352 190 103 145 269 280 151 10000 3048 2625 8612 200 370 200 108 150 278 290 157 10500 3200 2750 9022 220 407 250 135 155 287 300 162 11000 3353 2875 9432 240 444 300 162 160 296 310 167 11500 3505 3000 9843 260 482 350 189 165 306 320 173 12000 3658 3125 10253 280 519 400 216 170 315 330 17...

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Page 29: ...ly 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 k...

Page 30: ... 95 psi 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 pressur...

Page 31: ...200 lbs Acro 850 kg 1874 lbs Maximum landing weight Utility 999 kg 2200 lbs Acro 850 kg 1874 lbs 2 7 WEIGHT AND CENTER OF GRAVITY ENVELOPE Reference planes for CG calculations vertical firewall horizontal straight part of cockpit frame 2 7 1 UTILITY FLIGHT Maximum takeoff weight Forward CG Rear CG 999 kg 2200 lbs 550 mm 21 65 in 25 700 mm 27 55 in 33 2 7 2 ACROBATIC FLIGHT Maximum takeoff weight F...

Page 32: ...imited 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 Maneuvers Recommended entry speeds IAS Symbol Remarks Min kts km h Max kts km h Horizontal line VS 225 417 Aileron Roll VS 225 417 45 climbing 80 148 225 417 90 up 174 322 225 ...

Page 33: ...n performing maneuvers at speeds above VA 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 ...

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Page 35: ... 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 maximu...

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Page 37: ... only On right cockpit wall Near eyeball air vents On right cockpit wall Below compass For N 30 60 E 120 150 Steer For S 210 240 W 300 330 Steer DATE VHF ON OFF AIRPATH On right cockpit wall Behind pilot seat and On instrument panel front instrument panel On fuel quantity indicator Near fuel filler caps On canopy frame rh Near canopy locking lever inside front and back Outside ...

Page 38: ...ircraft with Airspeed indicators in knots On baggage compartment Near fuselage and Wing tank drains On oil inspection flap For aircraft with Airspeed indicators in km h Near smoke refill connector Left wheelpant inner side Near vent fuselage underside On left rear cockpit wall near G Meter Under the Airspeed indicator ...

Page 39: ... psi to 95 psi yellow arc 95 psi to 115 psi red line 115 psi Oil temperature indicator green arc 100 F to 245 F red line 245 F Fuel pressure indicator yellow arc 0 psi to 12 psi green arc 12 psi to 65 psi red line 65 psi Manifold pressure indicator green arc 11 in Hg to 32 in Hg Cylinder head temperature indicator Operating Range 200 F to 465 F Starts to flicker when exceeding max temperature Tach...

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Page 41: ... 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 Ve...

Page 42: ...t M M M O Optional M Mandatory The asterisks used in the above list requires a detailed observation of the 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 du...

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Page 45: ...rmed 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 ...

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Page 47: ...ximum 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 APPLY BRAKES When insufficient runway is left Harsh 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 O...

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Page 49: ...l temperature and oil pressure OBSERVE Power REDUCE When oil pressure drops below 25 psi engine must be stopped If oil pressure drops to zero Propeller goes to high pitch low RPM low drag High oil temperature Oil pressure CHECK When oil temperature rises and oil pressure sinks REDUCE POWER If possible INCREASE airspeed 3 3 5 ALTERNATOR FAILURE AND WIRE FIRE Alternator failure Alternator switch OFF...

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Page 51: ...necessary PUSH Fine pitch Malfunctions 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 80 KIAS 150 km h Propeller PULL COARSE PITCH Best glide ratio E 7 Prop at fine pitch pushed reduces the glide ratio to E 5 5 Loss of oil pressure puts the prop to coarse p...

Page 52: ...FF 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...

Page 53: ...EN 3 9 EMERGENCY EXIT AFTER FLIP OVER Master switch OFF Fuel selector valve OFF Pull 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 t...

Page 54: ...3 24 01 2011 3 11 LIGHTNING STRIKE In case the aircraft gets struck by a lightning Engine Propeller Vibration REDUCE RPM if necessary Airspeed REDUCE TO 110 kts Load factors AVOID higher loads than 1 2 0 8G Controlability ASSESS HANDLING If satisfactory LAND ASAP If not BAIL OUT ...

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Page 57: ...l 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 ...

Page 58: ...lage 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 Verti...

Page 59: ...t and play CHECK I 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...

Page 60: ...kin for damage CHECK O Canopy Canopy frame and glass to damage CHECK P Left main gear Main gear strut to damage CHECK Tyre to pressure and wear CHECK Tire and wheel slip mark CHECK Q Left wing leading edge Wing leading edge and skin for damage CHECK Fuel cap and fuel capacity CHECK Left wing tank DRAIN Pitot tube for choking and damage CHECK R Left wing trailing edge Spade and spade arm CHECK Aile...

Page 61: ...ITCH Mixture PUSH FULL RICH Throttle FULL OPEN Electric fuel pump ON 3 sec Throttle IDLE PUSH 3mm OPEN Mixture CUT OFF Elevator PULL Brake APPLY Propeller area FREE CHECK and CALL Starter ENGAGE When engine starts to fire FEED IN MIXTURE 1000 rpm with throttle ADJUST Oil pressure CHECK must rise within 30 sec Avionic switch ON Warm up 2 min 1000 rpm CHECK Afterwards 1500 rpm ADJUST Until oil tempe...

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Page 63: ...eller control PUSH FINE PITCH Throttle to 1700 rpm ADJUST Magnetos 1 2 CHECK Max RPM drop 175 rpm CHECK Max RPM difference 50 rpm CHECK Propeller control 3 x PULL COARSE PITCH Afterwards PUSH FINE PITCH Throttle to Idle RPM 700 rpm ADJUST Controls free CHECK 4 6 2 TAKEOFF Normal takeoff Throttle FULL OPEN 30 kts lift tail wheel PUSH 75 kts LIFTOFF 90 kts CLIMB Takeoff in crosswind Throttle FULL OP...

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Page 65: ...00 rpm ADJUST Manifold pressure AS REQUIRED Set Mixture according to EGT Indicator ADJUST Select right left wing tank every 30 min SWITCH 4 9 LANDING PROCEDURES 4 9 1 DESCENT Mixture PUSH FULL RICH Fuel selector valve to acrobatic tank ACRO SWITCH Electric fuel pump ON Power during descent RPM min 2000 rpm ADJUST Manifold pressure AS REQUIRED Watch CHT to prevent excessive cooling Airspeed AS REQU...

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Page 67: ... TOUCHDOWN Elevator pulled 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 80 kts 150 km h Approach speed with power 70 kts 130 km h Three point attitude TOUCHDOWN Brakes APPLY as needed 4 9 7 AFTER LANDING Electrical fuel pump OFF Elevator pulled KEEP 4 10 SHUTDOWN Throttle IDLE Avionic Switch OFF...

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Page 69: ...owed 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 ...

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Page 71: ...n be entered with any required speed between VS und VNE 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 VNE 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 Ful...

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Page 73: ...ive 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 deflec...

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Page 77: ...r 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 ...

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Page 79: ...rplane Flight Manual XA42 AFM XA42 0040 002 A 01 Page date Page 2 24 01 2011 Chapter 05 5 2 ISA CONVERSION ISA Conversion of pressure altitude and outside air temperature are shown in the following figure ...

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Page 81: ... 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 roll 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 ...

Page 82: ...99 kg Lift off speed 70 KIAS 130 km h Speed over 50 ft obstacle V50 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 0 SL Take off run 216 236 256 278 over 50 ft obstacle 351 372 404 438 1000 Take off run 229 249 271 294 over 50 ft obstacle 360 393 427 464 2000 Take off run 242 264 287 312 over 50 ft obstacle 381 416 452 4...

Page 83: ...2 over 50 ft obstacle 224 244 265 287 1000 Take off run 150 163 178 193 over 50 ft obstacle 236 257 280 304 2000 Take off run 159 173 189 205 over 50 ft obstacle 251 273 297 323 3000 Take off run 168 183 200 217 over 50 ft obstacle 265 289 315 342 4000 Take off run 178 194 212 230 over 50 ft obstacle 280 306 334 363 5000 Take off run 189 206 225 244 over 50 ft obstacle 297 325 354 385 6000 Take of...

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Page 85: ...FORMANCE 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 Best power mix Economy mix Limit 75 Press Alt OAT ISA RPM MP TAS FF Endurance Range FF PWR Endurance Range ft C C 1 min Hg kts L h h min NM L h h NM 4 000 9 9 2100 21 0 167 42 5 30 920 37 45 6 20 1050 4 000 9 9 2300 23 0 178 54 4 05 73...

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Page 87: ...Landing distances 999 kg Landing weight Pressure altitude Distance Temperature C ft m ISA ISA 10 ISA 20 ISA 30 0 SL Landing run 428 461 496 532 over 50 ft obstacle 710 765 823 883 1000 Landing run 443 478 515 552 over 50 ft obstacle 736 794 854 916 2000 Landing run 460 496 534 573 over 50 ft obstacle 763 823 886 951 3000 Landing run 477 514 554 595 over 50 ft obstacle 791 854 919 988 4000 Landing ...

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Page 89: ...cle 468 505 543 583 2000 Landing run 292 316 340 365 over 50 ft obstacle 485 524 564 605 3000 Landing run 303 327 352 379 over 50 ft obstacle 503 543 585 628 4000 Landing run 314 340 366 393 over 50 ft obstacle 522 564 607 652 5000 Landing run 326 352 380 408 over 50 ft obstacle 541 585 630 678 6000 Landing run 338 366 395 424 over 50 ft obstacle 561 607 655 704 7000 Landing run 351 380 410 441 ov...

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Page 91: ...d 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 ...

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Page 93: ...fication Weight change Added Removed Operational empty weight Weight kg Arm m Moment kg m Weight Kg Moment kg m Empty weight as delivered 6 3 CENTER OF GRAVITY CALCULATION SAMPLE 6 3 1 Sample Left main wheel Mlmw 294 0 kg Right main wheel Mrmw 305 4 kg Tail wheel Mtw 53 7 kg Empty weight ME Mlmw Mrmw Mtw 653 1 kg Main wheels vertical reference plane A 118 mm Tail wheel vertical reference plane B 4...

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Page 95: ... 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 lbs Kg x m inch x lbs 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...

Page 96: ...ITS Example At 900kg 1984 lbs and 56700 kgcm 49203 in lbs CG Location is 63 cm 24 8 in aft of Reference Datum UTILITY FLIGHT Maximum takeoff weight Forward CG Rear CG 999 kg 2200 lbs 550 mm 21 65 in 25 700 mm 27 55 in 33 ACROBATIC FLIGHT Maximum takeoff weight Forward CG Rear CG 850 kg 1874 lbs 550 mm 21 65 in 25 700 mm 27 55 in 33 ...

Page 97: ...ol ACS Products A 920 67 5 0 50 0 65 R 1 1 Propeller Spinner MT Propeller MT Propeller MTV 9 B C C203 20d 30 50 0 80 1 22 1 35 R R 1 Governor MT Propeller P 880 5 1 30 0 95 R 1 1 Cowling bottom Cowling top XtremeAir GmbH XtremeAir GmbH XA42 7110 150 XA42 7110 152 5 80 3 60 0 65 0 65 R R 1 Canopy XtremeAir GmbH XA42 5210 050 13 10 1 50 R 1 Main Tank Assy XtremeAir GmbH XA42 2810 050 5 10 0 20 R 2 M...

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Page 99: ...S 533 0 22 1 15 R 1 Altimeter front Altimeter back United Instruments 5934PM 34 84 0 37 1 15 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 Fun...

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Page 103: ...ressure 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 one piece Lateral loads and t...

Page 104: ...r 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 ...

Page 105: ... 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 1 2 3 4 5 6 9 10 30 11 12 13 18 19b 19 20 21 22 23 24 25 26 27 28 14 15 16 17 8 7 ...

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Page 107: ...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 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 s...

Page 108: ...il wheel is a swivel mounted solid rubber wheel Main landing gear wheels have a size of 5 00 Main landing 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 adjustab...

Page 109: ...e 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 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...

Page 110: ...ng 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 P...

Page 111: ...mounted in and supported by the tank compartment of the fuselage The two wing tanks are located in the inner 3 compartments wing root 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 ball out and corresponding bank 0 5 L 0 13 US ga...

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Page 113: ... 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 Fig 7 11 2 Fuel Selector Volt direct current system Power is supplied by a gear driven alternator with regulator field is switched via alternator switch which feeds the onboard In case of emergency the batter...

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Page 115: ...eeds 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 a...

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Page 119: ...ropeller 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 ...

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Page 121: ...ffects 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 fuse...

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Page 125: ... Chapter 09 24 01 2011 9 SUPPLEMENTS LOG OF EFFECTIVE PAGES Issue Chapter 09 Page I and Chapter 09 Page 1 1 A 01 Chapter09 Page 2 1 and Chapter 09 Page 2 2 A 01 TABLE OF CONTENT Supplement No Title Installed 9 1 EMERGENCY LOCATION TRANSMITTER 9 2 TRANSPONDER TRT 800 H ...

Page 126: ...ing 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 Control...

Page 127: ... 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 ...

Page 128: ...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 options After power ON the display shows the name of the instrument and the software version as shown in Fig 9 2 7 2 Fig 9 2 7 2 power ON display Operations Transponder Mode Selection Press MOD repeatedly to select from the following modes ACS Standard condition transponder responds to...

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