Aquila A212 GX Pilot Operating Handbook Download

Page: 31 / 145

POH

AQUILA AT01-200C

SECTION 3

EMERGENCY PROCEDURES

Document Nr.:

Issue:

Supersedes Issue:

Date:

Page:

FM-AT01-1010-106

A.01

--- (first issue)

02.03.2020

3 - 2

3.11

FLAP CONTROL SYSTEM MALFUNCTIONS

3-20

3.12

TRIM CONTROL SYSTEM FAILURES

3-20

3.12.1

3.12.2

Trim System Inoperative

Trim Actuator Runaway

3-20

3-21

3.13

AVIONICS MALFUNCTIONS

3-21

3.13.1

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

Magnetometer Failure

Complete Navigation System Failure

AHRS Failure

ADC Failure

Complete MVP-50P-AQ Failure

3-21

3-22

3-23

3.14

STARTER MALFUNCTION

3-24

3.15

IN-FLIGHT FAILURES AND MALFUNCTIONS

3-24

3.15.1

Inadvertent Release and Opening of the Canopy in flight

3-24

Summary of Contents for A212 GX

Page 1: ...ssue 02 03 2020 Certified according to JAR VLA 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 revisions The aircraft must be operated in compliance with the procedures and operating limits stated herein ...

Page 2: ...EASA 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 presented in loose leaf form to ease the substitution of revisions and is sized in A5 format for convenient storage in the aircraft Tab dividers throughout the handbook allow quick reference to each section A Table of Co...

Page 3: ...rst issue 02 03 2020 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 approved section 5 WEIGHT AND BALANCE 6 AIRCRAFT DESCRIPTION 7 HANDLING AND MAINTENANCE 8 SUPPLEMENTS 9 ...

Page 4: ...ted the list of resulting effective chapters can be found in chapter 9 Section Issue Approved Page Date 0 A 01 0 1 to 0 6 02 03 2020 1 A 01 1 1 to 1 12 02 03 2020 2 A 01 X 2 1 to 2 10 02 03 2020 3 A 01 X 3 1 to 3 24 02 03 2020 4 A 01 X 4 1 to 4 20 02 03 2020 5 A 01 X 5 1 to 5 24 02 03 2020 6 A 01 6 1 to 6 14 02 03 2020 7 A 01 7 1 to 7 26 02 03 2020 8 A 01 8 1 to 8 6 02 03 2020 9 A 01 9 1 to 9 2 02...

Page 5: ... an existing section will be identified by a vertical black 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 version Generally only complete sections of the POH will be exchanged and not individual pages The operation of the AQUILA AT01 is only permitted...

Page 6: ...T01 200C Section 0 Document Nr Issue Supersedes Issue Date Page FM AT01 1010 106 A 01 first issue 02 03 2020 0 5 Revision A 01 of POH ref FM AT01 1010 106 is approved under the authority of the DOA ref EASA 21J 025 ...

Page 7: ... 200 related Manuals and Publications AQUILA Aviation International GmbH OT Schönhagen 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 914 F related Manuals and Publications Contact the ROTAX authorized distributor for ROTAX Aircraft Engines of the applicable distribution area For contact det...

Page 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 4 1 5 AQUILA AT01 200 THREE VIEW DRAWING 1 5 1 6 ENGINE 1 6 1 7 PROPELLER 1 6 1 8 FUEL 1 6 1 9 OIL AND COOLANT 1 7 1 9 1 1 9 2 Engine Oil Engine Coolant 1 7 1 8 1 10 WEIGHTS 1 8 1 11 TERMINOLOGY AND A...

Page 9: ... GPS and others is included in Section 9 Supplements of this Manual Information regarding equipment approved for installation in the AQUILA AT01 200 is provided in Section 6 of this manual and in the approved equipment overview list in the Maintenance Manual Document Number MM AT01 1020 110 1 2 AIRCRAFT TYPE CERTIFICATION The aircraft AQUILA AT01 is type certified in accordance with the certificat...

Page 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 or destruction of equipment if not strictly adhered to The issues addressed under these text boxes have an indirect or minor impact on the airworthiness and the safe operation of the aircraft NOTE Ca...

Page 11: ...t 7 87 ft 2 40 m 1 4 2 Wings Airfoil HQ XX mod Area 113 02 sq ft 10 50 m Aspect Ratio 10 10 Mean Aerodynamic Chord MAC 3 51 ft 1 07 m 1 4 3 Horizontal Stabilizer Elevator Area 21 52 sq ft 2 00 m Span 9 84 ft 3 00 m 1 4 4 Fuselage and Vertical Stabilizer Rudder Maximum Fuselage Width 3 94 ft 1 20 m Length 24 28 ft 7 40 m Area Vertical Tail 14 39 sq ft 1 33 m 1 4 5 Landing Gear Wheel Track 6 37 ft 1...

Page 12: ...POH AQUILA AT01 200C Section 1 GENERAL Document Nr Issue Supersedes Issue Date Page FM AT01 1010 106 A 01 first issue 02 03 2020 1 5 1 5 AQUILA AT01 200 THREE VIEW DRAWING ...

Page 13: ...5 Diameter 68 9 in 175 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 Fuel Tank Fuel Capacity total 15 8 US gal 60 l 15 8 US gal 60 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 1 37 US gal 5 2 l Due to the higher lead conten...

Page 14: ... the ROTAX Service Instruction SI 914 019 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 CAUTION Do not use aviation grade oil When operating the engine with AVGAS do not use full synthetic oil If the engine is operated extensively on AVGAS 100LL more than 30hrs within 100hrs the interval betwee...

Page 15: ... 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 54 US quarts 2 4 l Maximum 2 64 US quarts 2 5 l Overflow Bottle Minimum 0 106 US quarts 0 1 l Maximum 0 21 US quarts 0 2 l 1 10 WEIGHTS Maximum Takeoff Weight MTOW 1653 lb 750 kg Maximum Landing Weight...

Page 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 aircraft relative to the ground VA Maneuvering Speed VS Stall speed without engine power VS0 Stall speed without engine power in the landing configuration VX Best Angle of Climb Speed VY Best Rate of Climb S...

Page 17: ...ff weight and basic empty weight Usable Fuel Fuel available for flight planning Unusable fuel Fuel remaining in the fuel tanks that cannot be safely used in flight Center of Gravity C G The point at which the aircraft would balance if it were possible to suspend it at that point MAC mean aerodynamic chord MTOW maximum takeoff weight MWL maximum landing weight MZFW empty weight 1 11 3 Meteorologica...

Page 18: ...s 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 Reference System GDU Garmin Display Unit MFD Multi Function Display AI Attitude Indicator or Artificial Horizon LDG Flaps landing position T O Flaps takeoff position UP Flaps cruise position MP Manifold Pressure ...

Page 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 0 454 kg 1 12 5 Volume 1 US Gallon 3 78 Liter 1 Imperial Gallon 4 546 Liter 1 12 6 Temperature t C Celsius 5 9 t F 32 t F Fahrenheit 9 5 t C 32 ...

Page 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 6 WEIGHT LIMITS 2 6 2 7 CENTER OF GRAVITY LIMITS 2 6 2 8 MANEUVER LIMITS 2 6 2 9 FLIGHT LOAD FACTORS 2 7 2 10 CREW 2 7 2 11 KINDS OF OPERATION LIMITS MINIMUM EQUIPMENT 2 8 2 12 FUEL LIMITATIONS 2 9 2 13 TEMPERATURE LIMITATIONS 2 9 2 14 OPERATING ...

Page 21: ...anel 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 Indicated Airspeeds IAS the airspeed shown on the airspeed indicator Indicated Airspeed IAS kts Remarks VA Maneuvering speed 112 Do not make full or abrupt control movements above this speed This may result in overloadi...

Page 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 914 F3 NOTE The engine is equipped with a hydraulic propeller governor and drives the propeller via a reduction gearbox The gearbox reduction ratio is 2 43 1 The tachometer indicates the propeller speed As a result all rpm readings in this manual are expressed a...

Page 23: ...sure Maximum MCP 35 inHg Maximum TOP 5 min 40 inHg g Oil Temperature Maximum 266 F 130 C Minimum 122 F 50 C h Cylinder Head Temperature CHT Maximum 248 F 120 C i Minimum temperature to start the engine Minimum 13 F 25 C At an OAT below 13 F 25 C the engine must be preheated 2 4 2 Propeller a Manufacturer mt Propeller Entwicklung GmbH Atting Germany b Model MTV 21 A 175 05 c Propeller diameter 68 9...

Page 24: ...reen Arc normal operating range Yellow Arc caution Red Line maximum Tachometer RPM 535 2260 2260 2385 2385 Oil Temperature F C 122 50 122 266 50 130 266 130 Cylinder Head Temperature F C 248 120 Oil Pressure psi bar 11 6 0 8 29 72 5 2 0 5 0 11 6 29 0 8 2 0 72 5 101 5 5 0 7 0 101 5 7 0 Fuel Pressure psi bar 2 2 0 15 2 2 5 1 0 15 0 35 5 1 0 35 Manifold Pressure inHg 0 35 35 40 40 Voltmeter V 11 12 5...

Page 25: ...g leading edge at the fuselage wing junction With 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 0 523m aft of Datum WARNING Exceeding the center of gravity limits is prohibited Exceeding the limits reduces the controllability and stability of the ai...

Page 26: ...ed while performing any approved maneuvers Flight 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 Maneuvers that include intentional negative flight load factors are not permitted Intentional Spinning is not permitted 2 10 CREW Maximum number of people on b...

Page 27: ...each occupied seat Emergency Hammer Battery 34 Ah Alternator ALT 2 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 flown In Germany a watch with a seconds hand may be used as a working timepiece Please observe all differing national regulations In Germany...

Page 28: ...on within section 4 NORMAL PROCEDURES NOTE The fuel quantity fuel used and fuel remaining functions of the G500 TXi MVP 50 are advisory information only and must be verified by the pilot 2 13 TEMPERATURE LIMITATIONS Parts of the aircraft structure that are exposed to direct vertical sunlight must be painted WHITE The cooling system of the engine was certified up to ISA 23 C For climbing in OAT hig...

Page 29: ...M AT01 1010 106 A 01 first issue 02 03 2020 2 10 2 15 PLACARDS 1 On the instrument panel in the lower middle section of the panel 2 On the instrument panel below the Airspeed Indicator 3 On the inner surface of the baggage compartment door 4 On the instrument panel next to the main switches ...

Page 30: ...3 4 FORCED LANDINGS 3 10 3 4 1 3 4 2 Precautionary Landing Emergency Landing 3 10 3 11 3 5 SMOKE AND FIRE 3 11 3 5 1 3 5 2 3 5 3 3 5 4 Engine Fire on the Ground Engine Fire in Flight Electrical Fire with Smoke on the Ground Electrical Fire with Smoke in Flight 3 11 3 12 3 12 3 12 3 6 INADVERTENT FLIGHT INTO ICING CONDITIONS 3 13 3 7 SPIN RECOVERY PROCEDURE 3 13 3 8 POWER OFF GLIDE 3 14 3 9 LANDING...

Page 31: ... MALFUNCTIONS 3 21 3 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 Magnetometer Failure Complete Navigation System Failure AHRS Failure ADC Failure Complete MVP 50P AQ Failure 3 21 3 21 3 21 3 22 3 22 3 22 3 23 3 23 3 23 3 14 STARTER MALFUNCTION 3 24 ...

Page 32: ...ways 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 considered a recommendation for the following emergency procedures Applicable for all switches pushing the top ON pushing the bottom OFF CAUTION A tripped circuit breaker or safety switch should only be res...

Page 33: ...g 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 following items if time allows 2 Fuel selector valve SWITCH to fullest or other tank 3 Fuel Pump AUX switch ON 4 Ignition switch BOTH 5 Throttle wide OPEN 6 Propeller control lever START position 7 Choke PRESS OFF 8 ...

Page 34: ...een range and the oil temperature remains normal 2 Land at the nearest airfield If oil pressure sinks below the green range and the oil temperature rises 2 Throttle REDUCE to min required for flight 3 Precautionary landing PERFORM see 3 4 1 Engine may fail suddenly C LOSS OF FUEL PRESSURE 1 Fuel Pump AUX switch ON 2 Fuel selector valve SWITCH to fullest or other tank 3 Throttle REDUCE to min requi...

Page 35: ...TCU warning light YELLOW is blinking waste gate is not closing 1 Throttle KEEP manifold pressure in green range 2 Propeller control lever KEEP RPM in green range 3 TCU switch OFF Cover up switch down 4 TCU circuit breaker PULL 5 TCU circuit breaker after 5 seconds PRESS 6 TCU switch after 10 seconds TCU self test completed ON switch up If the situation does not improve 7 Precautionary landing PERF...

Page 36: ...E to min required for flight 2 Propeller control lever KEEP RPM in green range If manifold pressure cannot be reduced 3 Throttle wide OPEN increase engine power until engine is running as calm as possible 4 Propeller control lever KEEP RPM in green range When safe approach altitude for nearest landing field is reached 5 Perform emergency landing with engine off according to section 3 4 2 WARNING I...

Page 37: ...t waste gate position without a working TCU there is only a distinctly reduced engine power available G EXCEEDANCE OF THE MAXIMUM ALLOWABLE MANIFOLD PRESSURE OR OF THE MAXIMUM DURATION FOR OPERATION WITH TAKE OFF POWER I BOOST warning light RED is illuminated Exceedance of max manifold pressure 40inHg 1 Throttle KEEP manifold pressure in green range 2 Propeller control lever KEEP RPM in green rang...

Page 38: ... power is restored 10 Oil pressure CHECK 11 Choke PUSHED OFF 12 Electrical equipment SWITCH ON as required 13 Oil temperature CHECK NOTE The engine can also be restarted by Windmilling if the airspeed is increased to approx 120 kts Approx 1000 ft 300 m of altitude is required in this method I ENGINE RESTART PROCEDURE WITH WINDMILLING PROPELLER At airspeeds above 60 kts the propeller continues to w...

Page 39: ...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 or divert to an airfield The procedure for a precautionary landing is fundamentally the same as a normal landing which is described in Section 4 The choice of the landing field is here of particular ...

Page 40: ...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 Flaps in UP position 70 KIAS 2 Fuel selector valve OFF 3 Ignition switch OFF 4 Seat belts and harnesses TIGHT 5 COM ATC REPORT location and intention 6 ALT1 BAT switch OFF 7 ALT2 BAT2 switch OFF 8 ELT if necessary activate manually WARNING Wi...

Page 41: ...talled USE as required 3 5 4 Electrical Fire with Smoke in Flight 1 ALT1 BAT switch OFF 2 ALT2 switch OFF BAT2 still ON 3 Avionics switch OFF 4 All switches except Ignition OFF 5 Cabin ventilation and canopy slide window OPEN 6 Fire extinguisher if installed Use only if smoke persists 7 Land immediately Refer to Section 3 4 Forced Landings After landing and aircraft comes to a halt 8 Engine Shut d...

Page 42: ...rfaces 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 inaccurate with ice accumulation on the leading edge of the wing Additionally the stall warning system may be inoperative or may not work correctly 3 7 SPIN RECOVERY PROCEDURE 1 Rudder Full deflecti...

Page 43: ... 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 opposite the defective tire This allows the use of the entire runway width to correct any directional changes caused by the defective tire for example left tire defective land on the right side of the runway...

Page 44: ...s calm as possible 6 Propeller control lever below MCP marking 7 Precautionary Landing PERFORM see 3 4 1 Engine may fail suddenly WARNING In case of a complete electrical system failure the Main fuel pump is automatically separated from the remaining on bord power supply by a relay It is supplied with electricity from Alternator 2 directly In this condition the TCU is not controlling the turbochar...

Page 45: ...rcuit breaker CHECK if PULLED 7 ALT2 Disconnect circuit breaker CHECK if PULLED 8 Brightness level of all additional instruments not necessary for the safe continuation of the flight has to be reduced to half or the instruments have to be turned off 9 Ammeter and voltmeter MONITOR 10 Precautionary Landing PERFORM see 3 4 1 WARNING The MAIN fuel pump is no longer supplied with electricity in case a...

Page 46: ...ry for the safe continuation of the flight has to be reduced to half or the instruments have to be turned off 6 Ammeter and voltmeter MONITOR 7 Precautionary Landing PERFORM see 3 4 1 NOTE The remaining Alternator 2 ALT 2 is delivering approx 15A into the on board power supply and a properly maintained and fully charged battery alone is able to supply all necessary systems with electricity for at ...

Page 47: ...to be turned off 8 Ammeter and voltmeter MONITOR 9 Precautionary Landing PERFORM see 3 4 1 WARNING The MAIN fuel pump is no longer supplied with electricity in case alternator 2 ALT2 has failed and the fuel pump is separated from the remaining on board power supply by turning ALT2 switch off In this case the AUX fuel pump is the only fuel supply for the engine NOTE The remaining Alternator 1 ALT1 ...

Page 48: ...D Do not fly before problem is eliminated B In flight voltmeter values YELLOW or RED 1 All non essential equipment OFF until value turns from YELLOW to GREEN or from RED to YELLOW 2 If the value remains YELLOW or RED CHECK ammeter for defective alternator s for ALT1 ALT2 acc section 3 10 2 for ALT1 acc section 3 10 3 for ALT2 acc section 3 10 4 C During approach and landing voltmeter value YELLOW ...

Page 49: ...h switch through all positions 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 with the flaps not in the landing position stall speed and landing distance increase 3 12 TRIM CONTROL SYSTEM FAILURES 3 12 1 Trim System Inoperative 1 Elevator Trim circui...

Page 50: ...ICS 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 Receive Mode Failure of COM Equipment 1 Push to Talk PPT switch CHECK if pilot s and co pilot s PTT switches are not pressed or jammed also check transceiver display CHECK connectors 2 Head set Momentari...

Page 51: ...titude GPS altitude Transponder altitude ground visibility Heading Track Compass GPS ground track Airspeed GPS ground speed stall warning 3 13 5 Magnetometer Failure 1 Navigation via GPS ground track NOTE In the event of a magnetometer failure a red X will be displayed over the course display If the GDU 1060 is receiving a valid GPS ground track signal the magnetic heading display will be replaced...

Page 52: ...a 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 Certain functions such as TAS and wind calculation are no longer usable 3 13 9 Complete MVP 50P AQ Failure 1 Engine Instr 1 circuit breaker see 3 1 1 RESET if tripped If the MVP 50P AQ failure cannot be corrected maintain power settings...

Page 53: ...uring flight 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 corrected Do not unbuckle the seat belt in order to close the canopy During solo flights carefully try to close the canopy without neglecting flight tasks and pilot responsibilities If this is not...

Page 54: ...PECTION 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 Taxiing Taxiing Before Take off at the Taxi Holding Position Take off Climb Cruise Descent Landing Go Around Balked Landing After Landing Engine Shutdown Refueling Flight in Rain and or with Wing Contamin...

Page 55: ...ion 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 engine Type 914 series and the Operation and Installation Manual of mt Propeller ATA 61 01 024 Normal procedures associated with optional equipment can be found in Section 9 ...

Page 56: ...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 LANDING Airspeed IAS kts Final approach speed for landing Flaps LDG 60 Balked landing Flaps LDG 60 Maximum demonstrated crosswind component for take off or landing 15 Maximum airspeed with Flaps LDG VFE...

Page 57: ...ight wing drain and visually inspect for contamination 2 Gascolator drain drain and visually inspect for contamination A CABIN 1 Aircraft Documentation CHECK on board 2 Ignition key REMOVED 3 ALT1 BAT switch ON 4 Annunciator warning lights Press TEST check all ON 5 ALT1 switch OFF 6 Engine instruments CHECK 7 Fuel quantity CHECK 8 Nav Lights switch ON CHECK OFF 9 Landing Light switch ON CHECK OFF ...

Page 58: ...ue 02 03 2020 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 incorrect attachment foreign objects and general condition Control surfaces in addition check for free movement 1 2 3 4 5 6 7 8 ...

Page 59: ... 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 Fairing Visual inspection refer to 7 11 4 c Tire pressure and slip marking CHECK d Tire wheel brake Visual inspection e Chocks if in use REMOVE 5 Right wing a Entire wing surface upper and under side Visual...

Page 60: ...r Ignition ALT1 BAT switch and ALT2 BAT2 switch OFF Set the parking brake WARNING RISK OF BURNS Only check the oil and coolant levels when the engine is cool a 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 CAUTION NEVER turn the propeller against the direction of engine rotation Stop turning the propeller whe...

Page 61: ... d Cooler intake oil water intercooler CHECK if free from obstructions e Cowling Visual Inspection CHECK Camloc fasteners f Propeller and Spinner Visual inspection g Propeller blades CHECK for cracks and other damage 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 warning tone is audible e BAT...

Page 62: ...e is cool 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 oil tank This is indicated 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 and max markings The difference between min a...

Page 63: ...eating 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 movement then PUSH OFF 13 Choke CHECK for free movement and automatic reset 14 Throttle CHECK for free movement and if 100 indexed position is perceptible then set IDLE 15 Propeller Control Lever CHECK for free movement then...

Page 64: ...ttle IDLE 11 Propeller Control Lever HIGH RPM position 12 Avionics Switch OFF 13 P S Heat if installed OFF 14 Circuit Breakers CHECK all set NOTE Cage the Attitude Indicator if installed before switching ALT1 BAT on 15 ALT1 BAT switch ON NOTE Pay attention to messages that may appear on the PFD and MFD displays while the system is loading The attitude indicators AHRS module and stand by indicator ...

Page 65: ...ow rising values within 10 seconds after engine start otherwise shut down the engine immediately NOTE The starter may not be operated for more then 10 seconds at a time Allow the starter to cool off for at least 2 minutes between attempts CAUTION BAT2 switch must be turned ON at all times during flight to ensure a stabilized control voltage at the ALT2 regulator rectifier unit If the on board powe...

Page 66: ...S TEST and check that the ALT1 RED ALT2 RED ENG YELLOW ENG RED TCU YELLOW BOOST RED and P S HEAT YELLOW warning lights illuminate 4 Engine instruments CHECK NOTE Oil can be brought up to temperature during taxiing 5 Voltmeter CHECK if GREEN 6 ALT1 switch OFF ammeter ALT2 5A ALT2 OK 7 BAT1 switch OFF CHECK voltmeter if GREEN BAT2 OK 8 BAT1 switch ON 9 ALT1 switch ON ammeter ALT2 0A ALT1 OK 10 Ammet...

Page 67: ...7 Throttle SET 1700 RPM 8 Ignition switch Magneto check SWITCH 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 no RPM drop if TCU OK 10 Carburetor temperature indicator slight rise in temperature 11 Carburetor heat PUSH OFF 12 Propeller control lever SWITCH 3 times between HIGH RP...

Page 68: ...ON For the shortest take off distance over a 50 feet obstacle at sea level 7 Rotate speed 50 KIAS 8 Climb speed VX 52 KIAS 4 5 7 Climb 1 Throttle max 5 minutes WIDE OPEN 40 inHg afterwards 100 MCP 35 inHg 2 Propeller control lever max 5 minutes 2385 RPM afterwards 2260 RPM 3 Engine instruments CHECK if in GREEN range NOTE During take off and climb at take off power the yellow ENG warning light ill...

Page 69: ...1 3 Flaps switch UP 4 Trim switch SET as required 5 P S Heat switch if installed AS REQUIRED OFF AT OAT 59 F 15 C 6 Engine instruments CHECK if in GREEN range 7 Carburetor temperature indicator MONITOR CAUTION When carburetor temperature is around 32 F 0 C Carburetor heat should be applied and engine power should be increased appropriately to prevent carburetor icing 4 5 9 Descent 1 Throttle First...

Page 70: ...equired CAUTION In strong headwinds or crosswinds in turbulent air or in wind shear it may be desirable to approach using less flaps and at a higher airspeed 4 5 11 Go Around Balked Landing 1 Propeller control lever First START 2 Throttle Second WIDE OPEN 3 Carburetor Heat PUSH OFF 4 Flaps switch T O 5 Airspeed 65 KIAS CAUTION Continued operation with throttle wide open and carburetor heat engaged...

Page 71: ...on Switch OFF 8 ALT2 BAT2 switch OFF 9 Electrical equipment OFF 10 ALT1 BAT switch OFF NOTE The GARMIN G500 TXi and the MVP 50P AQ are turned off with the ALT1 BAT switch 11 Chocks and tie downs AS REQUIRED 4 5 14 Refueling 1 Engine Shutdown as in Section 4 5 13 2 Ground the aircraft CAUTION During refueling the aircraft must be grounded for example at the end of the exhaust pipe 3 Open fuel tank ...

Page 72: ...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 performance cruising speed and stall characteristics The stall speed may increase up to 3 kts and the air speed indicator may give false readings Visibility may deteriorate considerably in rain ...

Page 73: ...POH AQUILA AT01 200C Section 4 NORMAL PROCEDURES Document Nr Issue Supersedes Issue Date Page FM AT01 1010 106 A 01 first issue 02 03 2020 4 20 intentionally left blank ...

Page 74: ...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 Airspeed Cruise Power Settings Maximum Endurance Maximum Range Descent Fuel Consumption Time and Distance Landing Distance Climb Performance after Go Around Balked Landing Flight Planning Example 5 3 5 ...

Page 75: ...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 the procedures specified in this manual are followed The fuel flow data for cruise presented here are based on the recommended RPM manifold pressure setting for each altitude However fuel flow and th...

Page 76: ...ion accounts for the position error of the pitot static pressure system but not for the instrument error Assumption zero instrument error Example 120 KIAS indicated airspeed corresponds to 118 KCAS calibrated airspeed Fig 5 2 1 Airspeed Calibration 30 40 50 60 70 80 90 100 110 120 130 140 150 160 170 180 190 200 30 40 50 60 70 80 90 100 110 120 130 140 150 160 170 180 190 200 KCAS KIAS flap LDG fl...

Page 77: ...8 in 427 mm behind the Ref Datum Takeoff mass 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 Stall Speeds kts NOTE Stalling speed with bank angle should be considered as for reference purposes only Slight differences in how the aircraft stalls can lead to discrepancies The greater the angle o...

Page 78: ...e FM AT01 1010 106 A 01 first issue 02 03 2020 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 uncontrollable crosswind component kt headwind component kt ...

Page 79: ...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 wing contamination can cause errors of up to 10 when calculating range and endurance NOTE Insects or other contamination on the propeller or the leading edge of the wing can significantly reduce the per...

Page 80: ...0 800 900 1000 0 50 Take off Distance Ground Roll Obstacle Height ft m ft Do not interpolate at altitudes between 0 and 50 ft Conditions Throttle Full Throttle max 5 min Prop Speed 2385 rpm Flaps T O Notes For operations on dry mown grass runway increase ground roll distance by 25 on soft grass runway up to 40 Snow and slush require an appropriate increase in ground roll In high humidity condition...

Page 81: ...Service Ceiling ISA Best Rate of Climb Speed KIAS 1764 800 16 400 ft 1653 750 16 400 ft 1323 600 16 400 ft Document Nr Issue Supersedes Issue Date Page FM AT01 1010 106 A 01 02 03 2020 5 8 MSL 2000 ft 4000 ft 6000 ft 8000 ft 10000 ft 12000 ft 14000 ft 22 4 14 32 50 68 86 104 30 20 10 0 10 20 30 40 Outside Air Temperature F Outside Air Temperature OAT C 1320 1370 1420 1470 1520 1570 1620 1670 1720 ...

Page 82: ...itude ft Fuel Time Distance liters min NM Vy 66 KIAS up to 5000 ft Vy 64 KIAS up to 10 000 ft Vy 61 KIAS up to 16 400 ft Fuel Time Distance Conditions 2260 rpm MCP Flaps UP m 800 kg 1764 lb no wind 6 1 1 1 5 0 liters 1 32 US gal 13 1 2 4 10 7 min 10 42 15 4 2 7 12 7 NM Example Airport Pressure Altitude 1800 ft Cruising Flight Pressure Alt 9500 ft see also page 5 18 For each 8 C above ISA increase ...

Page 83: ...020 5 2 8 Cruising Speed TAS True airspeed Flying without any wheel fairings or with mud guards reduces performence up to 10 22 4 14 32 50 68 86 104 0 2000 4000 6000 8000 10000 12000 14000 16000 30 20 10 0 10 20 30 40 Outside Air Temperature F Density Altitude ft Outside Air Temperature C Pressure Altitude A 95 100 105 110 115 120 125 130 135 140 145 150 155 True Airspeed KTAS 65 75 MCP Performanc...

Page 84: ... 2180 32 2 25 0 6 6 2260 35 28 0 7 4 6000 3 37 1820 28 16 0 4 3 1990 29 20 0 5 2 2080 31 23 0 6 1 2185 32 2 25 0 6 6 2260 35 28 0 7 4 8000 1 30 1830 28 17 0 4 5 2000 29 20 5 5 4 2090 31 23 0 6 1 2195 32 2 25 0 6 6 2260 35 28 5 7 5 10 000 5 23 1850 28 18 0 4 7 2005 29 21 0 5 5 2100 31 23 5 6 2 2200 32 2 25 5 6 8 2260 35 28 5 7 5 12 000 9 16 1865 28 18 5 4 9 2010 29 21 5 5 6 2105 31 23 5 6 2 2210 32...

Page 85: ... at 55 2 11 US gal 8 l Example Pressure Altitude 9500 ft Density Altitude 10000 ft Power Setting 75 Endurance 4 31 h 4 h 19 Outside Air Temperature 32 F 0 C FM AT01 1010 106 A 01 02 03 2020 5 12 POH AQUILA AT01 200C Section 5 PERFORMANCE Document Nr Issue Supersedes Issue Date Page 3 0 3 5 4 0 4 5 5 0 5 5 6 0 6 5 Endurance h 55 65 75 Perform 85 MCP n 2260 22 4 14 32 50 68 86 104 0 2000 4000 6000 8...

Page 86: ...g at 55 2 11 US gal 8 l Example Pressure Altitude 9500 ft Density Altitude 10000 ft Power Setting 75 Range 541 NM Outside Air Temperature 32 F 0 C FM AT01 1010 106 A 01 02 03 2020 5 13 POH AQUILA AT01 200C Section 5 PERFORMANCE Document Nr Issue Supersedes Issue Date Page 22 4 14 32 50 68 86 104 0 2000 4000 6000 8000 10000 12000 14000 16000 30 20 10 0 10 20 30 40 Outside Air Temperature F Density ...

Page 87: ...persedes Issue Date Page 0 1 2 3 4 5 6 7 8 9 10 11 12 13 0 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000 11000 12000 13000 14000 15000 16000 0 2 4 6 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 44 46 48 50 Fuel US gallons Pressure Altitude ft Fuel Time Distance litres min NM Fuel Note The values shown are for calm conditions The chart is valid for all permissible masses and outside ai...

Page 88: ...ction 5 PERFORMANCE Landing Mass lbs kg Airspeed KIAS 1764 800 1653 750 1323 600 Document Nr Issue Supersedes Issue Date Page FM AT01 1010 106 A 01 02 03 2020 5 15 0 250 500 750 1000 1250 1500 1750 2000 2250 2500 2750 3000 3250 0 100 200 300 400 500 600 700 800 900 1000 0 50 Ground Roll Landing Distance Obstacle Height ft m ft 22 4 14 32 50 68 86 104 30 20 10 0 10 20 30 40 Outside Air Temperature ...

Page 89: ...n 5 PERFORMANCE Take off Mass lbs kg Airspeed KIAS 1764 800 62 1653 750 57 1323 600 55 Document Nr Issue Supersedes Issue Date Page FM AT01 1010 106 A 01 02 03 2020 5 16 MSL 2000 ft 4000 ft 6000 ft 8000 ft 10000 ft 12000 ft 14000 ft 22 4 14 32 50 68 86 104 30 20 10 0 10 20 30 40 Outside Air Temperature C 1320 1370 1420 1470 1520 1570 1620 1670 1720 300 350 400 450 500 550 600 650 700 750 800 850 9...

Page 90: ...uise conditions Overall flight distance to destination 480 NM 888 km Cruise altitude altimeter setting 1013 hPa 9500 ft Temperature at cruise altitude 32 F 0 C 9 F 5 C above ISA in 9500 ft Reported wind en route 10 kts tailwind component Conditions at the destination airfield Pressure altitude 380 ft Temperature 68 F 20 C 11 F 6 C above ISA in 380 ft RWY direction 27 270 Wind conditions 220 15 kts...

Page 91: ...o the cruise altitude 9500 ft Since the outside air temperature is up to 13 F 7 C above ISA the values determined must be increased by 10 and because of the lower take off mass decreased by 15 For our example we obtain the following Climbing time 13 1 2 4 1 1 0 85 10 0 min 10 00 Climbing distance 15 4 NM 2 7 NM 1 1 0 85 11 9 NM Fuel required 6 1 ltr 1 1 ltr 1 1 0 85 4 7 ltr 1 61 US gal 0 29 US gal...

Page 92: ...ximum possible flight endurance is obtained from chart 5 2 10 on page 5 12 In our example the maximum endurance is 4 31 hours 4 h 19 min at a power setting of 75 This maximum flight endurance and the maximum flight range determined above include 30 minutes of reserve at a power setting of 55 engine start up taxiing take off climb cruise descent and landing Taking the reported tailwind of 10 kts in...

Page 93: ...e time spent in cruise we obtain 441 1 NM 139 kts 3 17 h 3 h 10 min The fuel required for the cruise segment is 3 17 h x 6 21 US gal h 23 5 l h 19 69 US gal 74 5 ltr A fuel flow of 6 21 US gal h 23 5 l h is calculated from the table on page 5 11 in the section for the power setting of 75 MCP as follows Option 1 For a temperature of 32 F 0 C at 9500 ft we obtain a density altitude of 10000 ft refer...

Page 94: ...0 kts does 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 13 on page 5 15 Once again use chart 5 2 3 on page 5 5 to determine the wind components relative to the runway Relative to the runway heading the wind is 50 from the left at 15 kts This gives a...

Page 95: ...he runway is calculated as follows 𝟓𝟓𝟓𝟓 𝒇𝒇𝒇𝒇 𝟖𝟖𝟖𝟖𝟖𝟖 𝒇𝒇𝒇𝒇 𝒎𝒎𝒎𝒎𝒎𝒎 𝟓𝟓𝟓𝟓𝟓𝟓𝟓𝟓 𝒇𝒇𝒇𝒇 𝒎𝒎𝒎𝒎𝒎𝒎 𝟑𝟑𝟒𝟒𝟒𝟒 𝒇𝒇𝒇𝒇 𝟏𝟏𝟏𝟏𝟏𝟏 𝒎𝒎 The result does not include any safety factor and should be used as an estimation only For safety reasons the decision for a go around must be made earlier than the calculated value In the event of a turbocharger failure a climb rate of 420 ft min can be determined from diagram 5 2 14 which r...

Page 96: ... Supersedes Issue Date Page FM AT01 1010 106 A 01 first issue 02 03 2020 5 23 5 3 NOISE CHARACTERISTICS ABATEMENT Certification basis Actual MTOW 750kg 1653 lbs Maximum Allowable CS 36 Amendment 5 62 7 dB A 74 2 dB A ICAO Annex 16 Chapter 10 62 7 dB A 74 2 dB A ...

Page 97: ...POH AQUILA AT01 200C Section 5 PERFORMANCE Document Nr Issue Supersedes Issue Date Page FM AT01 1010 106 A 01 first issue 02 03 2020 5 24 intentionally left blank ...

Page 98: ...T WEIGHING 6 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 Weight and Moment Determination Approved Center of Gravity Range and Moment Limits Estimating Center of Gravity Position using MVP 50P AQ 6 8 6 9 6 10 6 11 6 5 EQUIPMENT LIST 6 12 6 5 1 Current Equipment...

Page 99: ...2 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 regulations at regular intervals or after repairs after extensive maintenance after large portions of the aircraft have been painted after changes to the equipment or when doubt exists as to the accuracy of...

Page 100: ... 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 DSL Distance of C G to Reference Datum BE Aircraft Weighing Example in kg m Position Weight kg Lever m Moment kg m Nose Wheel mB 106 DB 0 840 MB 89 Left Main Wheel mL 200 DL 0 780 ML 156 Right Main W...

Page 101: ...d signed off by an authorized person It is important that the Weight and Balance Record be complete and up to date The first entry in the record is made during the conformity inspection at the end of the manufacturing process NOTE The pilot uses the 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...

Page 102: ...POH AQUILA AT01 200C Section 6 WEIGHT AND BALANCE Document Nr Issue Supersedes Issue Date Page FM AT01 1010 106 A 01 first issue 02 03 2020 6 5 Replace with current Aircraft Weighing Report ...

Page 103: ...taff 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 single mass kgm or lb in Registration Sign lever of single mass m or in single mass kg or Lb in flight direction aft of BE front of BE or AQUILA AT01 description of the change at delivery OUT IN Date ...

Page 104: ...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 Record and enter them into the appropriate fields of Table 6 4 2 Weight and Moment Determination 2 Using chart 6 4 1 Loading Graph determine the moments of the load pilot fuel baggage etc Enter this inf...

Page 105: ...taken into consideration The moments for the forward and the aft seat positions are shown the moments for all other positions must be interpolated Gepäck Kraftstoff 0 20 40 60 80 100 120 140 160 180 200 220 240 0 10 20 30 40 50 60 70 80 90 100 110 120 130 140 Moment of loading kg m lb ft Loading Graph Seat most forward Seat most rearward baggage fuel 530 485 440 395 350 305 265 220 175 130 90 45 0...

Page 106: ...seat middle BAGGAGE 51 2 1 3 33 15 1690 20 Weight Moment without fuel 1490 676 28230 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 30265 346 Explanation Transfer the empty weight and the empty C G DSL from section 6 3 1 or from the current Aircraft Weighing Report Add all the weights Transfer the moments from chart 6 4 1 or calcula...

Page 107: ...70 580 590 600 610 620 630 640 650 660 670 680 690 700 710 720 730 740 750 760 230 240 250 260 270 280 290 300 310 320 330 340 350 360 370 380 390 400 410 420 1665 1810 1950 2100 2240 2380 2530 2680 2820 2970 1675 1650 1630 1610 1585 1565 1540 1520 1500 1475 1455 1435 1410 1390 1365 1340 1320 1300 1280 1255 1230 1210 435 455 475 495 515 Moments of mass kg m lb in Flight mass kg lbs xS 16 8 in 17 1...

Page 108: ...f 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 in section 6 4 of this POH The current empty weight of the aircraft as programmed by an authorized maintenance organization and registered in section 6 3 1 is an absolutely essential input to ensure c...

Page 109: ...tions 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 provided in the Maintenance Manual The retrofitting of equipment must be conducted in accordance with the applicable Service Bulletin When in doubt the type certificate holder or the production organization of AQUILA Aviation should ...

Page 110: ... issue 02 03 2020 6 13 6 5 1 Current Equipment List of the Aircraft AQUILA AT01 200 Registration S N AT01 200C Designation Description Manufacturer Model P N S N Installation Location Mark where applicable Describe installation location or enter lever arm from reference datum in in keep algebraic sign of lever arm in mind ...

Page 111: ...T01 1010 106 A 01 first issue 02 03 2020 6 14 AQUILA AT01 200 Registration S N AT01 200C Designation Description Manufacturer Model P N S N Installation Location Mark where applicable Describe installation location or enter lever arm from reference datum in in keep algebraic sign of lever arm in mind ...

Page 112: ...ING 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 7 8 7 7 1 7 7 2 7 7 3 7 7 4 Overview Control Panel Cabin Heat Cabin Ventilation Additional lighting NVFR 7 9 7 9 7 9 7 10 7 8 SEATS SEATBELTS AND HARNESSES 7 10 7 9 BAGGAGE COMPARTMENT 7 10 7 10 CANOPY 7 11 7 11 L...

Page 113: ...ECTRICAL 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 7 22 7 15 GLASS PANEL ENGINE MONITOR MVP 50P 7 22 7 15 1 7 15 2 Engine Monitoring Instruments Voltmeter and Amperemeter 7 22 7 23 7 16 ANNUNCIATOR PANEL 7 23 7 16 1 7 16 2 7 16 3 7 16 4 7 16 5 7 16 6 Warning Light ALT 1 Warning Light ALT 2 Warnin...

Page 114: ...in G500 TXi System Primary Flight Display The GARMIN G500 TXi system has 2 displays the PFD and the MFD Together they form the Garmin Display Unit GDU In addition the GDU requires an Attitude and Heading Reference System AHRS unit and an Air Data Computer ADC unit The GARMIN G500 TXi display has an integrated AHRS and the ADC is installed directly onto the back side of the GDU The GARMIN G500 TXi ...

Page 115: ... 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 limit The MVP 50P AQ system is attached to the aircraft power supply via a push pull circuit breaker which is located on the right side of the instrument panel and is labeled MOTOR INSTR 1 The MVP 50P ...

Page 116: ...ure The engine side the firewall which is made of a GFRP CFRP sandwich is covered with a special fire resistant ceramic fleece and a stainless steel sheet The landing gear frame together with the seat frame supports the main landing gear struts The frame continues upwards and forms a massive roll cage made from GFRP and CFRP 7 4 WING The wing is designed with a triple trapezoid planform and a swep...

Page 117: ... elevator deflection The trim system is an electrically actuated spring trim Even in a situation such as trim runaway the aircraft remains controllable though the stick forces may become somewhat higher The trim is controlled by a spring loaded switch The trim indicator is located in the middle of the instrument panel The take off position of the trim is marked on the indicator Switch forward nose...

Page 118: ...p operation A flap position indicator is also located on the instrument panel In cruise position the upper green light is illuminated UP In take off position the middle green light is illuminated T O In landing position the lower green light is illuminated LDG The flap selector switch position corresponds accordingly to the flap position Stripe markings on the flap leading edge offer an additional...

Page 119: ...1 GARMIN G500 TXi 5 ALT2 BAT2 9 ACL 13 Reserved 17 ELT 21 Glass Panel Engine Monitor MVP 50P AQ 2 Stby artificial horizon 6 Fuel Pump AUX 10 Landing Light 14 Flap Control Switch 18 TCU switch 3 Ignition Switch 7 Avionics 11 Instrument Lights opt 15 Compass 19 COM NAV GPS 22 Circuit Breakers 4 ALT1 BAT 8 Nav Light 12 P S Heat opt 16 Annunciator Panel 20 Transponder 23 Ventilation Nozzle NOTE The ac...

Page 120: ...ich 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 windshield defrosting and cabin heating 7 7 3 Cabin Ventilation Two adjustable ventilation nozzles are located on both sides of the instrument panel to supply fresh air to the cabin The amount and direction of fresh air...

Page 121: ...g strut must be unlocked by pushing a handle located by your thigh Both seats are equipped with four part seat belts with a central rotary buckle The shoulder harnesses are connected to inertial reels To fasten the seat belts put each belt fitting successively into the associated receptacles of the rotary buckle until a distinctive snap sound is heard The seat belts can be released by turning the ...

Page 122: ...d the 5 00 x 5 wheels on the nose and main wheels the AQUILA AT01 200 can be easily operated from a grass surface The aircraft can be operated with full size wheel pants or for soft field operation mud guards 7 11 1 Nose Landing Gear and Nose Wheel Steering The direct linkage between nose wheel and rudder pedals minimizes brake wear Good shock absorption and suspension characteristics are provided...

Page 123: ...se the parking brake push the parking brake lever all the way forward 7 11 4 Wheel Fairings It is important that no dirt or snow accumulate underneath the wheel pants For this reason the Aquila AT01 200 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 the l...

Page 124: ... which via a bowden cable adjusts a waste gate for manifold pressure and power control An additional intercooler for turbocharged air ensures that air temperature behind the turbocharger always remains within the operation limits of the engine Reduction ratio of internal gearbox 2 43 1 Displacement 73 9 in 1211 cm max takeoff power 5 min 113 3 BHP 84 5 kW at max takeoff propeller speed 2385 RPM ma...

Page 125: ...ler pitch propeller control lever position are normally matched to each other Refer to Section 5 of this manual and to ROTAX 914F Operator s Manual for more information During the final approach for landing the low pitch setting of the propeller is used to increase the propeller drag at low power settings and to have full climb power available in case of a missed approach throttle aft and propelle...

Page 126: ...e part of the dyadic bowden cable closes a cover on top of the intercooler The other part closes a flap in the air intake system behind the air filter so that the engine is then provided with pre heated intake air from the engine compartment The correct use of carburetor heat prevents the formation of carburetor ice that can cause the engine to run rough and in the worst case result in complete en...

Page 127: ...ngine Monitor 3 Coarse fuel filter element 11 Fuel filler cap 4 Gascolator fine filter Drain valve 12 Firewall 5 Electrical fuel pump AUX ALT1 BAT 13 Engine 6 Fuel selector shut off valve 14 Fuel level probe 7 Electrical fuel pump MAIN ALT2 15 Fuel pressure regulator pressure probe 8 Carburetor 16 By pass with check valve Fuel System Schematic MVP50P left wing tank right wing tank Fuel supply line...

Page 128: ...f and landing when low fuel pressure is suspected or during critical phases of flight Too low fuel pressure relative to the manifold pressure is detected by a pressure probe at the fuel pressure regulator and another one at the airbox The resulting fuel over pressure is displayed as fuel pressure on the MVP 50P AQ NOTE When flying near the ground such as during take off and landing or if low fuel ...

Page 129: ...L due to the dihedral angle Additionally a dipstick to visually verify the fuel 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 wing After pulling the dipstick out of the fuel tank the fuel level can be determined by the wetted area of the dipstick This...

Page 130: ... breaker The alternator ALT1 is air cooled and driven by a V belt drive geared down from the propeller shaft ALT2 is directly driven by the Propeller shaft If one alternator regulator fails one of the red alternator warning lights ALT1 or ALT2 located in the annunciator panel will illuminate The charging current of the battery as well as the produced current of the alternators are monitored by the...

Page 131: ...POH AQUILA AT01 200C Section 7 AIRCRAFT DESCRIPTION Document Nr Issue Supersedes Issue Date Page FM AT01 1010 106 A 01 first issue 02 03 2020 7 20 Fig Electrical System Schematic 1 2 ...

Page 132: ...POH AQUILA AT01 200C Section 7 AIRCRAFT DESCRIPTION Document Nr Issue Supersedes Issue Date Page FM AT01 1010 106 A 01 first issue 02 03 2020 7 21 Fig Electrical System Schematic 2 2 ...

Page 133: ...ature 12 Charging current ALT1 ALT2 4 Oil pressure 13 Time 5 Cylinder head temperature 14 Up down timer 6 Fuel level in each tank 15 Flight time 7 Total fuel capacity 16 Engine operating hours 8 Fuel pressure 17 Estimated c g 9 Carburetor temperature 18 OAT optional The keys of the MVP 50P AQ have the following functions Select press to move the cursor select functions and change data or values Ex...

Page 134: ...ELLOW values will be shown During normal operation this is a sign of an alternator malfunction The charging current of each alternator is displayed on the separate amperemeters ALT1 and ALT2 7 16 ANNUNCIATOR PANEL The warning lights ALT1 ALT2 BOOST TCU ENG YELLOW ENG RED P S HEAT optional and TEST test switch are incorporated in the annunciator panel 7 16 1 Warning Light ALT1 The red alternator wa...

Page 135: ...FF switched down 7 16 4 Warning Light BOOST The red BOOST warning light should not illuminate during normal operation The RED warning light illuminates only if Exceeding the maximum manifold pressure The RED warning light flashes only if Exceeding the maximum time for take off power 7 16 5 Warning Light ENG YELLOW RED The warning light ENG YELLOW appears as soon as a value in the MVP 50P AQ reache...

Page 136: ... 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 and ALT2 BAT2 switch ON Start up engine in accordance with section 4 5 2 Engine Start up Disconnect external power source 7 18 PITOT STATIC SYSTEM A pitot static tube is installed on the lower surface of the left wing which via t...

Page 137: ...l 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 The switch generates a loud buzzing sound as long as this condition is maintained NOTE The stall warning system a small metal plate on the leading edge is delicate and must be handled with care 7 20 AVIONICS Depe...

Page 138: ... 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 Jacking 8 3 8 3 8 4 8 4 8 5 CLEANING AND CARE 8 5 8 5 1 8 5 2 8 5 3 8 5 4 8 5 5 Painted Surfaces Canopy Propeller Engine Interior Cleaning 8 5 8 6 8 6 8 6 8 6 ...

Page 139: ...umber MM AT01 1020 110 the Operation Manual of the ROTAX type 914 engine series and the Operation and Installation Manual of the propeller CAUTION If the engine is operated extensively on AVGAS 100LL more than 30 hrs within 100 hrs the interval between oil changes shall be reduced to 50 hrs 8 3 MODIFICATIONS AND REPAIRS Changes to the aircraft are only permissible with the approval of the competen...

Page 140: ...the vertical stabilizer to raise the nose wheel off the ground Now the aircraft 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 term parking align the aircraft into the wind retract the flaps set the parking brakes and chock the main wheels When park...

Page 141: ... by red circles It is recommended to always carry the eye bolts delivered with 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 lower surface of the wing at the wing root ribs Both of these jacking points are marked with a red ring The tail of the airc...

Page 142: ...d 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 difficult to remove them when dried Only use a mild detergent in cases where the dirt proves very hard to remove Care should be taken because even a mild detergent will gradually wash away the protective wa...

Page 143: ...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 Installation Manual E 124 from mt propeller 8 5 4 Engine Refer to current issue of the Operator s Manual for the ROTAX 914 series engine 8 5 5 Interior Cleaning Dust and dirt in the interior of the aircra...

Page 144: ...e 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 supplements for the AQUILA AT01 This table may be also used as a directory for this section adapted to your aircraft If modifications requiring an STC have been conducted on your aircraft at a Maintenance Organ...

Page 145: ...ation variable AST 01 Night VFR AT01 200C AS 09 Garmin GTN 650 AS 10 Garmin GMA 350 c AS 11 ELT Kannad 406 AS 14 Trig TT22 AS 17 Garmin GTR 225 225A 225B AS 18 Garmin GNC 255A 255B AS 19 Garmin GMA 340 AS 21 Garmin GTX 335 345 AS 22 Garmin G5 Stby AI AS 24 Traffic Sensor AT 1 NOTE For the devices listed above and marked with an software updates will be released on our website www aquila aviation d...

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Aquila A212 GX, Pilot Operating Handbook

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