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POH / AFM

AQUILA AT01-100C

Section 2

LIMITATIONS

Document Nr.:

Issue:

Supersedes Issue:

Date:

Page:

FM-AT01-1010-103

A.02

28.05.2013

15.10.2013

2 - 9

2.12 FUEL LIMITATIONS

Left Fuel Tank

Right Fuel Tank

Fuel capacity (total): 15.85 US gal (60.0 l)

15.85 US gal (60.0 l)

Usable fuel (total): 14.48 US gal (54.8 l)

14.48 US gal (54.8 l)

Unusable fuel:

1.37 US gal (5.2 l)

NOTE

The amount of unusable fuel was determined with flap on LDG and V

= 90 kts. It is the worst

case fuel supply configuration within section 4 “NORMAL PROCEDURES”.

For approved fuel grades, please refer to paragraph 1.8.

2.13 TEMPERATURE LIMITATIONS

Parts of the aircraft structure that are exposed to direct vertical sunlight must be painted
WHITE.

2.14 OPERATING ALTITUDE

The Aquila AT01-100 has a maximum operating altitude of 14,500 ft.

Содержание A211 GX

Страница 1: ...LA This Pilot s Operating Handbook POH must be carried on board the aircraft at all times The amendment history and revision status are provided in the list of effective pages and in the list of revis...

Страница 2: ...s handbook are EASA FAA approved and mandatory Failing to follow the procedures and limits set forth in this handbook can lead to a loss of liability by the manufacturer THE HANDBOOK The handbook is p...

Страница 3: ...2 15 10 2013 08 04 2014 0 2 TABLE OF CONTENTS SECTION GENERAL 1 OPERATING LIMITATIONS approved section 2 EMERGENCY PROCEDURES approved section 3 NORMAL PROCEDURES approved section 4 PERFORMANCE partly...

Страница 4: ...Section Issue Approved Page Date 0 A 03 0 1 to 0 6 08 04 2014 1 A 02 1 1 to 1 12 15 10 2013 2 A 02 X 2 1 to 2 10 15 10 2013 3 A 02 X 3 1 to 3 18 15 10 2013 4 A 02 X 4 1 to 4 20 15 10 2013 5 A 02 X 5 1...

Страница 5: ...line adjacent to the applicable revised area A new issue code appears in the footer of the revised pages If revisions are distributed the applicable sections are to be exchanged with the updated versi...

Страница 6: ...AT01 100C Section 0 Document Nr Issue Supersedes Issue Date Page FM AT01 1010 103 A 03 A 02 15 10 2013 08 04 2014 0 5 Revision A 03 of AFM ref FM AT01 1010 103 is approved under the authority of DOA r...

Страница 7: ...UILA Aviation GmbH OT Sch nhagen Flugplatz D 14959 Trebbin Tel 49 0 33731 707 0 Fax 49 0 33731 707 11 E Mail kontakt aquila aviation de Internet http www aquila aviation de b Engine ROTAX 912 S relate...

Страница 8: ...1 3 1 4 PRINCIPLE AIRCRAFT DIMENSIONS 1 4 1 4 1 1 4 2 1 4 3 1 4 4 1 4 5 Overall Dimensions Wings Horizontal Stabilizer Elevator Fuselage and Vertical Stabilizer Rudder Landing Gear 1 4 1 4 1 4 1 4 1...

Страница 9: ...arding equipment approved for installation in the AQUILA AT01 100 is provided in Section 6 of this manual and in the approved equipment overview list in the Maintenance Manual Document Number MM AT01...

Страница 10: ...strictly adhered to The issues addressed under these text boxes directly affect the airworthiness and the safe operation of the aircraft CAUTION Procedures practices etc which may result in damage to...

Страница 11: ...ght 7 87 ft 2 4 m 1 4 2 Wings Airfoil HQ XX mod Area 113 02 sq ft 10 5 m Aspect Ratio 10 1 Mean Aerodynamic Chord MAC 3 51 ft 1 07 m 1 4 3 Horizontal Stabilizer Elevator Area 21 52 sq ft 2 0 m Span 9...

Страница 12: ...UILA AT01 100C Section 1 GENERAL Document Nr Issue Supersedes Issue Date Page FM AT01 1010 103 A 02 28 05 2013 15 10 2013 1 5 1 5 AQUILA AT01 100 THREE VIEW DRAWING 2 4 m 7 87 ft 7 4 m 24 28 ft 10 3 m...

Страница 13: ...5 Diameter 66 9 in 170 cm 1 8 FUEL The following fuel grades are approved for use min RON 95 EN228 Super ASTM D4814 EN228 Super plus AVGAS 100LL ASTM D910 AVGAS UL 91 ASTM D7547 Left Fuel Tank Right F...

Страница 14: ...issue of the ROTAX Service Instruction SI 912 016 The following chart shows the recommended oil viscosity as a function of the climatic conditions The use of multi grade oils is recommended Figure 1 2...

Страница 15: ...re ratio anti freeze water 50 15 50 15 CAUTION Low quality or contaminated coolant may lead to deposits in the cooling system which may result in insufficient engine cooling Coolant Quantity Minimum 2...

Страница 16: ...evel KCAS CAS expressed in knots TAS True Airspeed the airspeed relative to undisturbed air which is the CAS corrected for altitude temperature and compressibility GS Ground speed speed of the aircraf...

Страница 17: ...the conduction of the takeoff run Useful Load Difference between takeoff weight and basic empty weight Usable Fuel Fuel available for flight planning Unusable fuel Fuel remaining in the fuel tanks th...

Страница 18: ...er GFRP Glass Fiber Reinforced Plastic CFRP Carbon Fiber Reinforced Plastic ACL Anti Collision light VFR Visual Flight Rules PFD Primary Flight Display ADC Air Data Computer AHRS Attitude and Heading...

Страница 19: ...NVERSION FACTORS 1 12 1 Length 1 ft 0 304 m 1 in 25 4 mm 1 12 2 Speed 1 kt 1 852 km h 1 mph 1 609 km h 1 12 3 Pressure 1 hPa 100 N m 1 mbar 1 in Hg 33 865 hPa 1 psi 68 97 mbar 1 12 4 Mass Weight 1 lb...

Страница 20: ...DICATOR MARKINGS 2 3 2 4 POWER PLANT LIMITATIONS 2 3 2 4 1 2 4 2 Engine Propeller 2 3 2 4 2 5 MARKINGS ON THE GLASS PANEL ENGINE MONITOR MVP 50P AQ 2 5 2 7 WEIGHT LIMITS 2 6 2 8 CENTER OF GRAVITY LIMI...

Страница 21: ...r the Glass Panel Engine Monitor MVP 50P AQ must be carried on board the aircraft and be accessible to the crew during flight 2 2 AIRSPEED LIMITATIONS The airspeeds given below are expressed in Indica...

Страница 22: ...Maximum speed for all operations 2 4 POWER PLANT LIMITATIONS 2 4 1 Engine a Manufacturer BRP ROTAX GmbH Co KG Gunskirchen Austria b Model 912 S3 NOTE The engine is equipped with a hydraulic propeller...

Страница 23: ...m 2 2 psi 0 15 bar Maximum 5 8 psi 0 40 bar f Oil Temperature Maximum 266 F 130 C Minimum 122 F 50 C g Cylinder Head Temperature CHT Maximum 264 F 129 C h Minimum temperature to start the engine Minim...

Страница 24: ...instrument markings shown on the MVP 50P AQ and their meaning MVP 50P AQ Red Line minimum Green Arc normal operating range Yellow Arc caution Red Line maximum Tachometer RPM 535 2260 2260 2385 2385 Oi...

Страница 25: ...th the aircraft leveled the reference datum and the vertical fall in a plane The center of gravity must be within the following limits Forward Limit 16 8 in 0 427m aft of Datum Rearward Limit 20 6 in...

Страница 26: ...t Load Factor g at VA at VNE With Flaps Extended Positive 4 0 4 0 2 0 Negative 2 0 2 0 0 WARNING Exceeding the flight load factors limits may result in damage to the aircraft structure CAUTION Maneuve...

Страница 27: ...Hammer The minimum equipment listed in Table 1 is valid for Germany Other countries may require different minimum equipment This may depend on the type of flight being carried out and the route being...

Страница 28: ...S gal 54 8 l Unusable fuel 1 37 US gal 5 2 l 1 37 US gal 5 2 l NOTE The amount of unusable fuel was determined with flap on LDG and VFE 90 kts It is the worst case fuel supply configuration within sec...

Страница 29: ...the lower middle section of the panel This aircraft is certified according to JAR VLA for day VFR operations under non icing conditions All aerobatic maneuvers including spins are prohibited For furt...

Страница 30: ...ailure 3 4 3 4 3 5 3 4 FORCED LANDINGS 3 7 3 4 1 3 4 2 Precautionary Landing Emergency Landing 3 7 3 8 3 5 SMOKE AND FIRE 3 8 3 5 1 3 5 2 3 5 3 3 5 4 Engine Fire on the Ground Engine Fire in Flight El...

Страница 31: ...13 1 3 13 2 3 13 3 3 13 4 3 13 5 3 13 6 3 13 7 3 13 8 3 13 9 Complete Avionics Failure Receive Mode Failure of COM Equipment Transmit Mode Failure of COM Equipment Primary Flight Display Failure Magne...

Страница 32: ...lways use good airmanship and have a sound knowledge of the aircraft and its systems 3 1 1 Resetting Circuit breakers The one time only resetting of a tripped circuit breaker or safety switch is consi...

Страница 33: ...r a forced landing must be initiated under consideration of the local conditions Turning back to the runway only at adequate altitude otherwise land straight ahead Pay attention to the speed Check the...

Страница 34: ...E 1 Oil Temperature CHECK If oil pressure sinks below the green range and the oil temperature remains normal 2 Land at the nearest airfield If oil pressure sinks below the green range and the oil temp...

Страница 35: ...wer is restored 9 Oil pressure CHECK 10 Choke PUSHED OFF 11 Electrical equipment SWITCH ON as required 12 Oil temperature CHECK NOTE The engine can also be restarted by Windmilling if the airspeed is...

Страница 36: ...autionary landing occurs when the pilot decides to discontinue flight to avoid a situation degrading into an emergency This way the pilot has time to make decisions and choose an adequate landing site...

Страница 37: ...rcraft In this case a pilot typically has significantly less time to choose a landing site compared with a precautionary landing 1 Airspeed Flaps in LDG position 60 KIAS Flaps in T O position 65 KIAS...

Страница 38: ...er if installed USE as required 3 5 4 Electrical Fire with Smoke in Flight 1 ALT1 BAT switch OFF 2 Avionics switch OFF 3 All switches except Ignition OFF 4 Cabin ventilation and canopy slide window OP...

Страница 39: ...faces periodically to keep them from freezing CAUTION The stall speed increases with ice accumulation on the wing leading edge Airspeed indicator altimeter and vertical speed indicator readings may be...

Страница 40: ...achievable in glide 3 9 LANDING WITH A FLAT TIRE When landing with a defective tire or this is suspected proceed as follows 1 Flaps LDG position 2 Perform touch down on the side of the runway opposit...

Страница 41: ...arning light is illuminated 1 ALT1 switch SWITCH OFF then ON approx 10 sec interval 2 ALT1 circuit breaker see 3 1 1 RESET if tripped If ALT1 warning light remains illuminated 3 ALT1 circuit breaker P...

Страница 42: ...OW or RED Do not fly before problem is eliminated B In flight Voltmeter value YELLOW 1 All non essential equipment OFF until value turns GREEN 2 If the value remains YELLOW Alternator is defective Pro...

Страница 43: ...s If the flap actuator is inoperative or the flap position indicator reading is incorrect approach and landing must be conducted at airspeed safe for the current flap setting WARNING During landings w...

Страница 44: ...ONICS MALFUNCTIONS 3 13 1 Complete Avionics Failure 1 Avionics switch SWITCH OFF then ON approx 20 sec interval If the switch trips to the OFF position 2 Land at the nearest suitable airfield 3 13 2 R...

Страница 45: ...tude Natural horizon Altitude GPS altitude Transponder altitude ground visibility Heading Track Compass GPS ground track Airspeed GPS ground speed stall warning 3 13 5 Magnetometer Failure 1 AHRS circ...

Страница 46: ...4 NOTE Failure of the Air Data Computers ADC is indicated through a red X and yellow text above the airspeed indicator the altimeter the vertical speed indicator the TAS and the OAT indicators Certai...

Страница 47: ...ht Even though the airflow conditions around the aircraft change considerably with an open canopy in flight the aircraft remains fully controllable Initial flight attitude changes can be easily correc...

Страница 48: ...SPECTION 4 9 4 5 CHECKLISTS FOR NORMAL PROCEDURES 4 11 4 5 1 4 5 2 4 5 3 4 5 4 4 5 5 4 5 6 4 5 7 4 5 8 4 5 9 4 5 10 4 5 11 4 5 12 4 5 13 4 5 14 4 5 15 Before Engine Start up Engine Start up Before Tax...

Страница 49: ...tion provides normal operating procedures and checklists for the aircraft as well as recommended airspeeds Additional information is provided in the current issues of the Operators Manual for ROTAX en...

Страница 50: ...r operational weight TAKE OFF Airspeed IAS kts Normal climb speed to 50 Feet Flaps T O 57 Best rate of climb speed at sea level Flaps UP VY 65 Best angle of climb speed at sea level Flaps T O VX 52 LA...

Страница 51: ...wing drain and visually inspect for contamination 2 Electrical fuel pump drain drain and visually inspect for contamination A CABIN 1 Aircraft Documentation CHECK on board 2 Ignition key REMOVED 3 AL...

Страница 52: ...13 15 10 2013 4 5 B EXTERIOR CHECK Visual Inspection CAUTION In this manual visual inspection means the following Inspect for mechanical damage dirt cracks delamination excessive play looseness leaks...

Страница 53: ...n CHECK fitting and bolt connection proper control cable connection and safe tied d Vertical stabilizer Visual inspection 4 Right main landing gear a Landing gear strut Visual inspection b Wheel Fairi...

Страница 54: ...dicated by the sound of air rushing from the open oil tank Use the oil dip stick to check that the oil level is between the min max markings The difference between min max is approximately 0 48 US Qua...

Страница 55: ...l inspection f Chocks and tow bar REMOVE 8 Left wing a Entire wing surface upper and under side Visual inspection b Fuel vent CHECK if clear c BAT switch ON d Stall warning press to upper detent warni...

Страница 56: ...4 Check oil level Turn the propeller several times in the direction of engine rotation to pump oil from the engine back into the oil tank Stop turning the propeller when air begins to return to the o...

Страница 57: ...ntrol locks remove 10 Seating position adjust and lock check that nose wheel steering and brakes can be operated 11 Carburetor heat CHECK for free movement then PUSH OFF 12 Cabin heat CHECK for free m...

Страница 58: ...ections 8 Fuel Selector Valve LEFT or RIGHT 9 Carburetor Heat PRESS 10 Throttle IDLE 11 Propeller Control Lever START position 12 Avionics Switch OFF 13 P S Heat if installed OFF 14 Circuit Breakers C...

Страница 59: ...ULL and keep pulled Hot Engine RELEASE automatic reset 5 Brakes PRESS both pedals 6 Propeller area CLEAR 7 Ignition switch START then BOTH 8 Oil Pressure CHECK if oil pressure rises CAUTION The oil pr...

Страница 60: ...en finished press the ENT button to save the changes 3 Annunciator panel PRESS TEST and check that the ALT1 ALT2 ENG YELLOW and ENG RED warning lights illuminate 4 Engine instruments CHECK NOTE Oil ca...

Страница 61: ...H through L BOTH R BOTH positions CHECK RPM drop max RPM drop 120 RPM max difference L R 50 RPM RPM drop must be noticeable then BOTH position 9 Carburetor heat PULL ON RPM drop 20 to 50 RPM 10 Carbur...

Страница 62: ...level 7 Rotate speed 50 KIAS 8 Climb speed VX 52 KIAS 4 5 7 Climb 1 Throttle WIDE OPEN 2 Propeller control lever max 5 minutes 2385 RPM afterwards 2260 RPM 3 Engine instruments CHECK if in GREEN range...

Страница 63: ...in GREEN range 7 Carburetor temperature indicator if installed MONITOR CAUTION During flights above a pressure altitude of 6000 ft the fuel pressure warning light must be monitored closely If the fue...

Страница 64: ...IAS 10 Propeller control lever START 11 Landing Light switch ON as required CAUTION In strong headwinds or crosswinds in turbulent air or in wind shear it may be desirable to approach using less flaps...

Страница 65: ...uipment OFF 8 ALT1 BAT switch OFF NOTE The GARMIN G500 and the MVP 50P AQ are turned off with the ALT1 BAT switch 9 Chocks and tie downs AS REQUIRED 4 5 14 Refueling 1 Engine Shutdown as in Section 4...

Страница 66: ...g Contamination CAUTION When flying with wet and or contaminated wings and control surfaces performance and handling qualities may be reduced This applies in particular to take off distance climb perf...

Страница 67: ...POH AFM AQUILA AT01 100C Section 4 NORMAL PROCEDURES Document Nr Issue Supersedes Issue Date Page FM AT01 1010 103 A 02 28 05 2013 15 10 2013 4 20 intentionally left blank...

Страница 68: ...5 2 15 Airspeed Calibration Stall Speeds Crosswind Component Flight Planning Take off Distance Climb Performance Cruise Altitude Climb Fuel Consumption Time and Distance Cruise Performance TAS True A...

Страница 69: ...andard Atmospheric conditions 59 F 15 C and 29 92 inHg 1013 25 hPa at sea level The performance data presented can be achieved with a well maintained aircraft and with average piloting techniques when...

Страница 70: ...10 2013 5 3 5 2 PERFORMANCE CHARTS 5 2 1 Airspeed Calibration Airspeed calibration accounts for the position error of the pitot static pressure system but not for the instrument error Assumption zero...

Страница 71: ...in 427 mm behind the Ref Datum Takeoff weight 1653 lb 750 kg Engine idle Flap Position Bank Angle 0 30 45 60 KCAS KIAS KIAS KIAS KIAS UP 52 49 51 55 64 T O 48 45 47 51 60 LDG 43 39 42 47 57 Tab 5 2 2...

Страница 72: ...013 15 10 2013 5 5 5 2 3 Demonstrated Crosswind Component Crosswind Diagram Maximum demonstrated crosswind component 15 knots 27 km h WARNING Stronger crosswind components may render the aircraft unco...

Страница 73: ...e conservative when reading diagrams and rounding values Differences between the actual performance data of the aircraft at hand and the data specified in this manual the influence of turbulence or wi...

Страница 74: ...ft Take off Weight 1587 lbs 720 kg Headwind 8 kts Take off roll 663 ft 202 m Outside Air Temperature 64 F 18 C Take off distance 1230ft 375 m Supersedes Issue Date Page Airspeed KIAS Take off Weight...

Страница 75: ...1323 600 A 02 Section 5 Performance Date POH AFM AQUILA AT01 100C Service Ceiling ISA 1653 750 Document Nr Supersedes Issue 14 500 ft Best Rate of Climb Speed KIAS 15 10 2013 Page FM AT01 1010 103 28...

Страница 76: ...0 45 50 Pressure Head ft Fuel Time Distance liter gallons min NM Time Fuel Conditions 2260 rpm MCP Flaps UP m 750 kg 1653 lb no wind For each 8 C above ISA increase time distance and fuel by 10 Distan...

Страница 77: ...ud guards reduces performance up to 10 FM AT01 1010 103 Issue A 02 Supersedes Issue 28 05 2013 Document Nr POH AFM AQUILA AT01 100C 2000 0 2000 4000 6000 8000 10000 12000 60 40 20 0 20 40 Density Alti...

Страница 78: ...44 1900 23 3 16 0 4 2 2100 23 3 16 8 4 44 2260 24 3 21 5 5 68 2260 25 2 22 0 5 81 5000 5 41 1950 22 7 16 5 4 4 2150 23 18 1 4 77 2260 23 8 21 9 5 79 6000 3 37 2000 22 0 17 0 4 7 2200 22 7 19 3 5 1 22...

Страница 79: ...5 l Example Pressure Altitude 4500 ft Density Altitude 5000 ft Power Setting 75 Endurance 4 55 h 4 h 33 Outside Air Temperature 50 F 10 C Page 5 12 Section 5 PERFORMANCE POH AFM AQUILA AT01 100C FM A...

Страница 80: ...l 7 5 l Example Pressure Altitude 4500 ft Density Altitude 5000 ft Power Setting 75 Range 537 NM Outside Air Temperature 50 F 10 C POH AFM AQUILA AT01 100C Section 5 PERFORMANCE Document Nr Issue Supe...

Страница 81: ...sue Date 15 10 2013 Page 5 14 0 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000 11000 12000 13000 14000 0 2 4 6 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 Pressure Head ft Fuel Time Distance...

Страница 82: ...ft Landing mass 1453 lbs 659 kg Headwind component 9 kts Landing distance 1230 ft 375 m Outside air temperature 68 F 20 C Ground roll 525 ft 160 m POH AFM AQUILA AT01 100C Section 5 PERFORMANCE Page I...

Страница 83: ...75 ft min Outside Air Temperature 25 C 77 F Supersedes Issue FM AT01 1010 103 A 02 28 05 2013 Date 15 10 2013 Section 5 PERFORMANCE POH AFM AQUILA AT01 100C Page 5 16 Document Nr Issue 30 20 10 0 10 2...

Страница 84: ...RWY 2040 ft 620 m Cruise conditions Overall flight distance to destination 480 NM 888 km Cruise altitude altimeter setting 1013 hPa 5000 ft Temperature at cruise altitude 50 F 10 C 7 F 4 C above ISA R...

Страница 85: ...el consumption to the cruise altitude 4500 ft Since the outside air temperature is 13 F 7 C above ISA the values determined must be increased by 10 For our example we obtain the following Climbing tim...

Страница 86: ...maximum possible flight endurance is obtained from chart 5 2 10 on page 5 13 In our example the maximum endurance is 4 52 hours at a power setting of 75 This maximum flight endurance and the maximum f...

Страница 87: ...458 35 NM With the expected 10 kts tail wind we obtain a estimated ground speed of 121 kts 10 kts 131 kts for the time spent in cruise we obtain kts 131 NM 458 35 3 50 h 3h 30 The fuel required for th...

Страница 88: ...es not materialize the power setting may have to be reduced to 65 MCP to achieve the same range with the same amount of fuel LANDING DISTANCE To determine the required landing distance use chart 5 2 1...

Страница 89: ...see chart 24 7 in Hg Manifold pressure calculated for ISA 10 C 24 7 24 7 x 0 03 25 4 in Hg Fuel consumption for ISA 4 3 US gal h 16 l h Fuel consumption calculated for ISA 10 C 4 3 4 3 x 0 05 4 5 US...

Страница 90: ...FT WEIGHING 2 3 6 3 WEIGHT AND BALANCE DATA 6 4 6 3 1 Weight and Balance Record 6 6 6 4 DETERMINING WEIGHT AND BALANCE FOR FLIGHT 6 7 6 4 1 6 4 2 6 4 3 6 4 4 Load moment determination loading graph We...

Страница 91: ...5 liters Unusable fuel 2 74 US Gal 10 4 liters b Equipment in accordance with the current equipment list section 6 5 NOTE The aircraft must be weighed in accordance with the relevant aviation regulat...

Страница 92: ...of the horizontal stabilizer Place a level on the wedge and level the aircraft Lever DB Distance from nose wheel to Reference Datum BE Lever DL DR Distance from main wheel to Reference Datum BE Lever...

Страница 93: ...empty weight C G as the basis for all weight and balance calculations for flight It is possible to calculate a new empty weight and C G if the changed weights and corresponding levers are known for ex...

Страница 94: ...POH AFM AQUILA AT01 100C Section 6 WEIGHT AND BALANCE Document Nr Issue Supersedes Issue Date Page FM AT01 1010 103 A 02 28 05 2013 15 10 2013 6 5 Replace with current Aircraft Weighing Report...

Страница 95: ...staff stamp signature S N empty weight and centre of gravity of the airplane center of gravity D SL m or in empty weight kg or Lb Mass Lever Moment of change acc to wing leading edge BE moment of sing...

Страница 96: ...d center of gravity and weight limits Proceed as follows 1 Take the basic empty weight mempty and the empty weight moment MOempty from the current Aircraft Weighing Report or the Weight and Balance Re...

Страница 97: ...taken in to consideration The moments for the forward and the aft seat positions are shown the moments for all other positions must be interpolated Gep ck Kraftstoff 0 20 40 60 80 100 120 140 160 180...

Страница 98: ...seat middle BAGGAGE 51 2 1 3 33 15 1690 20 Weight Moment without fuel 1490 676 27919 323 usable FUEL 6 01 lb US gal 0 72 kg l 12 8 0 325 159 26 5 gal 72 100 ltr 2035 23 Total Weight Moment 1649 748 29...

Страница 99: ...570 580 590 600 610 620 630 640 650 660 670 680 690 700 710 720 730 740 750 760 230 240 250 260 270 280 290 300 310 320 330 340 350 360 370 380 390 400 410 420 1665 1810 1950 2100 2240 2380 2530 2680...

Страница 100: ...of the values will be shown in red CAUTION The estimation of C G position using the MVP 50P AQ serves solely as additional information and is in no way a substitute for the proper calculation as shown...

Страница 101: ...e lever arms indicate locations in front of the reference datum NOTE The installation of additional equipment or a change in installed equipment must be carried out in accordance with the data provide...

Страница 102: ...05 2013 15 10 2013 6 13 6 5 1 Current Equipment List of the Aircraft AQUILA AT01 100 Registration S N AT01 100C Designation Description Manufacturer Model P N S N Installation Location Mark where appl...

Страница 103: ...AT01 1010 103 A 02 28 05 2013 15 10 2013 6 14 AQUILA AT01 100 Registration S N AT01 100C Designation Description Manufacturer Model P N S N Installation Location Mark where applicable Describe install...

Страница 104: ...LAGE 7 5 7 4 WING 7 5 7 5 EMPENNAGE 7 6 7 6 FLIGHT CONTROLS 7 6 7 6 1 7 6 2 7 6 3 7 6 4 Ailerons Elevator and Trim System Rudder Flaps and Flap Position Indication 7 6 7 6 7 6 7 7 7 7 INSTRUMENT PANEL...

Страница 105: ...el Level Indication 7 16 7 17 7 17 7 18 7 14 ELECTRICAL SYSTEM 7 19 7 14 1 7 14 2 7 14 3 Power Supply and Battery System Ignition System and Starter Electrical Equipment and Circuit Breakers 7 19 7 19...

Страница 106: ...Garmin Display Unit GDU In addition the GDU has an Attitude and Heading Reference System AHRS unit and an Air Data Computer ADC unit The GARMIN G500 system is organized as shown in the following illus...

Страница 107: ...n engine data converter ECD 33 and the attached probes When engine limits are exceeded the warning light ENG in the annunciator panel of the MVP 50P AQ will illuminate YELLOW caution or RED operating...

Страница 108: ...two half shells While the fuselage portion of the shell is fabricated from solid fiberglass laminate the vertical stabilizer portion has a sandwich structure On the engine side the firewall which is...

Страница 109: ...im system are electrically actuated 7 6 1 Ailerons The ailerons are controlled using push pull rods A bell crank in the middle of the main wing spar sets the differentiation of the ailerons Adjustable...

Страница 110: ...ed to allow the pilot to comfortably reach the rudder pedals 7 6 4 Flaps and Flap Position Indication The flaps are driven by an electric motor via a spindle and push pull rods A three position select...

Страница 111: ...ption No Description 1 GARMIN G500 5 Fuel Pump 9 Landing Light 13 Reserved 17 ELT 21 Glas Panel Engine Monitor MVP 50P AQ 2 Not Occupied 6 Avionics 10 Instrument Lights opt 14 Flap Control Switch 18 N...

Страница 112: ...knob by which the hot air flap is opened and closed is located in the forward section of the control panel At the front section of the instrument panel cover the heated air is divided up for windshiel...

Страница 113: ...COMPARTMENT The AQUILA AT01 100 incorporates a large baggage compartment behind the seats which can be loaded through a lockable baggage door The baggage compartment is also accessible through the ca...

Страница 114: ...are provided by a shock absorber made of stacked rubber springs located in the nose wheel fork The direct linkage between the nose wheel steering and rudder operation allows swift taxiing precise tax...

Страница 115: ...01 100 can be operated with either full wheel pants high speed with mud guards soft field or without any wheel fairings The aircraft can also be flown with a combination of wheel fairings as long as t...

Страница 116: ...ropeller Reduction ratio of internal gearbox 2 43 1 Displacement 82 5 in 1352 cm max takeoff power 5 min 98 6 BHP 73 5 kW at max takeoff propeller speed 2385 RPM max continuous power 92 5 BHP 69 0 kW...

Страница 117: ...are normally matched to each other Refer to Section 5 of this manual and to ROTAX 912S Operator s Manual for more information During the final approach for landing the low pitch setting of the propell...

Страница 118: ...tor heat push pull type control element is located on the control panel to the left of the choke and cabin heat The correct use of carburetor heat prevents the formation of carburetor ice that can cau...

Страница 119: ...Fuel pressure warning light 3 Coarse fuel filter element 10 Dual fuel level indicator 4 Fuel strainer 11 Fuel filler cap 5 Electrical fuel pump 12 Firewall 6 Fuel selector shut off valve 13 Engine 7...

Страница 120: ...50P AQ When the fuel pressure is low the electrical fuel pump must be turned on NOTE When flying near the ground such as during take off and landing or when low fuel pressure is indicated the electric...

Страница 121: ...l level is delivered with the aircraft With the aircraft horizontal the dip stick is inserted straight into the fuel tank so that the handle of the dipstick lays flat with the upper surface of the win...

Страница 122: ...circuit breaker The alternator is air cooled and driven by a V belt drive geared down from the propeller shaft If the alternator regulator fails the red alternator warning light ALT1 located in the a...

Страница 123: ...ANR COM 2 opt COM 2 Intercom Intercom TXP PFD ADC AHRS Transponder Traffic Monitor opt Traffic Monitor NAV GPS 1 NAV GPS 1 NAV GPS 2 NAV GPS 2 opt Avionics Dome Light Dome Light Panel Light Panel Ligh...

Страница 124: ...3 Oil temperature 12 Time 4 Oil pressure 13 Up down timer 5 Cylinder head temperature 14 Flight time 6 Fuel level in each tank 15 Engine operating hours 7 Total fuel capacity 16 Estimated c g 8 Fuel f...

Страница 125: ...he battery is supplying the electrical system of the aircraft YELLOW values will be shown During normal operation this is a sign of an alternator malfunction 7 16 ANNUNCIATOR PANEL The warning lights...

Страница 126: ...e that NO persons or objects are in the vicinity of the propeller disk Procedure for starting up the engine with an external power source Plug in and switch on the external power ALT1 BAT switch ON St...

Страница 127: ...e the stall is reached in all flap settings As the aircraft approaches a stalled condition a switch on the wing leading edge is activated due to a change in airflow as the angle of attack increases Th...

Страница 128: ...8 HANDLING SERVICE MAINTENANCE Page 8 1 INTRODUCTION 8 2 8 2 AIRCRAFT INSPECTION PERIODS 8 2 8 3 MODIFICATIONS AND REPAIRS 8 2 8 4 GROUND HANDLING 8 3 8 4 1 8 4 2 8 4 3 8 4 4 Towing Parking Tie Down J...

Страница 129: ...M AT01 1020 110 the Operation Manual of the ROTAX type 912 engine series and the mt propeller Operation and Installation Manual CAUTION If the engine is operated extensively on AVGAS 100LL more than 3...

Страница 130: ...ft can be pivoted around the main landing gear CAUTION 1 Never push pull or lift on the horizontal stabilizer or the spinner 2 Never push or lift the control surfaces and flaps 8 4 2 Parking For short...

Страница 131: ...the aircraft and suitable tie down ropes in the aircraft The tie down points should be covered with tape while flying to keep them clean 8 4 4 Jacking Two conical jacking points are located on the lo...

Страница 132: ...be washed regularly using plenty of water a clean sponge and chamois leather Severe contamination and dirt especially insects should be washed off immediately after every flight as it is more difficul...

Страница 133: ...able Always follow the manufacturer s instruction to ensure the desired results The inside of the canopy may be treated in the same way 8 5 3 Propeller Refer to current issue of the Operating and Inst...

Страница 134: ...iece of installed equipment Only the supplements that apply to the configuration of your aircraft must be contained in this section Section 9 2 Index of Supplements lists all existing approved supplem...

Страница 135: ...R AT01 100B AS 06 Night VFR AT01 100C AS 07 Garmin SL 40 AS 08 Garmin GTX 330 328 AS 09 Garmin GTN 650 AS 10 Garmin GMA 350 AS 11 ELT Kannad 406 AS 12 Garrecht TRX 1500 AS 13 Garrecht TRX 2000 AS 14 T...

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Содержание A211 GX

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Aquila A211 GX, Руководство по эксплуатации

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