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POH / AFM

AQUILA AT01-100C

Section 7

AIRCRAFT DESCRIPTION

Document Nr.:

Issue:

Supersedes Issue:

Date:

Page:

FM-AT01-1010-103

A.08

A.06 (01.06.2018)

25.05.2020

7 - 6

7.5 EMPENNAGE

The vertical and horizontal stabilizers, as well as the elevator and rudder are semi-monocoque
sandwich composite constructions. The shells are fabricated from a GFRP sandwich reinforced
by carbon fiber bands.
The horizontal stabilizer assembly is bonded directly to the fuselage and cannot be removed.

7.6 FLIGHT CONTROLS

The flight controls of the Aquila AT01-100 are of conventional design using a control column
and non-adjustable rudder pedals. The elevator and ailerons are controlled via push-pull-rods,
the rudder via cables.

The flaps and the trim 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 stops near the control column are used to limit the aileron deflection.

7.6.2 Elevator and Trim System

The elevator is controlled using push-pull-rods.

Adjustable stops near the control column are used to limit the 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 down

Switch aft:

nose up

In addition, the trim system is protected by a resettable circuit breaker.

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Содержание AT01-100C

Страница 1: ...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 presented in lo...

Страница 2: ...7 18 06 2019 25 05 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...

Страница 3: ...mented the list of resulting effective chapters can be found in chapter 9 Section Issue Approved Page Date 0 A 08 0 1 to 0 6 25 05 2020 1 A 08 1 1 to 1 12 25 05 2020 2 A 08 X 2 1 to 2 10 25 05 2020 3...

Страница 4: ...plicable 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...

Страница 5: ...T01 100C Section 0 Document Nr Issue Supersedes Issue Date Page FM AT01 1010 103 A 08 A 07 18 06 2019 25 05 2020 0 5 The technical content of this document is approved under the authority of the DOA r...

Страница 6: ...ed below a AQUILA AT01 100 related Manuals and Publications AQUILA Aviation International GmbH OT Sch nhagen Flugplatz D 14959 Trebbin Tel 49 0 33731 707 0 Fax 49 0 33731 707 11 E Mail kontakt aquila...

Страница 7: ...TES 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...

Страница 8: ...mation regarding 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 Numbe...

Страница 9: ...not 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...

Страница 10: ...Height 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...

Страница 11: ...LA AT01 100C Section 1 GENERAL Document Nr Issue Supersedes Issue Date Page FM AT01 1010 103 A 08 A 06 01 06 2018 25 05 2020 1 5 1 5 AQUILA AT01 100 THREE VIEW DRAWING 2 4 m 7 87 ft 7 4 m 24 28 ft 10...

Страница 12: ...0 05 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 Righ...

Страница 13: ...nt 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...

Страница 14: ...ture 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...

Страница 15: ...a level 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 airc...

Страница 16: ...keoff 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 a...

Страница 17: ...umber 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 Headi...

Страница 18: ...CONVERSION 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...

Страница 19: ...INDICATOR 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 LI...

Страница 20: ...lass 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 Indicated Air...

Страница 21: ...165 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 propel...

Страница 22: ...ature Maximum 266 F 130 C Minimum 122 F 50 C g Cylinder Head Temperature CHT Maximum 248 264 F 120 129 C h Minimum temperature to start the engine Minimum 13 F 25 C At an OAT below 13 F 25 C the engin...

Страница 23: ...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 248 264 120 129 O...

Страница 24: ...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 i...

Страница 25: ...ight 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 Mane...

Страница 26: ...for each occupied seat Emergency 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 bein...

Страница 27: ...d fuel grades please refer to paragraph 1 8 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 section 4 NORMAL PROCE...

Страница 28: ...in 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 f...

Страница 29: ...e Failure 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...

Страница 30: ...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 Mag...

Страница 31: ...always 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 con...

Страница 32: ...wer 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 t...

Страница 33: ...r KEEP RPM in green range When safe approach altitude for nearest landing field is reached 8 Perform emergency landing with engine off according to section 3 4 2 WARNING If the gas bowden cable is bro...

Страница 34: ...sential electrical equipment OFF 2 ALT1 BAT switch ON 3 Propeller control lever START position 4 Fuel selector valve SWITCH to fullest tank 5 Fuel Pump switch ON 6 Throttle warm engine OPENED 2 cm col...

Страница 35: ...nding the aircraft flips over an emergency hammer can be used to break through the canopy For this purpose an emergency hammer is attached to back of the right hand seat 3 4 1 Precautionary Landing NO...

Страница 36: ...nding occurs in a state of distress such as an engine failure fuel starvation or mechanical problems with the aircraft In this case a pilot typically has significantly less time to choose a landing si...

Страница 37: ...is running 2 Throttle IDLE 3 Fuel selector valve OFF 4 Ignition switch OFF 5 Canopy OPEN 6 Fire extinguisher if installed USE as required 3 5 4 Electrical Fire with Smoke in Flight 1 ALT1 BAT switch O...

Страница 38: ...START position 5 Cabin heat PULL ON 6 Move the control surfaces periodically to keep them from freezing CAUTION The stall speed increases with ice accumulation on the wing leading edge Airspeed indic...

Страница 39: ...nce 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 oppo...

Страница 40: ...1 warning 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 breake...

Страница 41: ...ELLOW 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...

Страница 42: ...ions 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 landing...

Страница 43: ...VIONICS 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...

Страница 44: ...ails Attitude 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...

Страница 45: ...13 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 Cer...

Страница 46: ...f during 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...

Страница 47: ...INSPECTION 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 T...

Страница 48: ...ection 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...

Страница 49: ...ower 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...

Страница 50: ...ht 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...

Страница 51: ...2018 25 05 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 lea...

Страница 52: ...ion 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 Fai...

Страница 53: ...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 max markings The difference between min max is approximately 0 48 U...

Страница 54: ...n e Shock absorber unit Visual 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 warnin...

Страница 55: ...ool 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 th...

Страница 56: ...Control 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 fre...

Страница 57: ...tions 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 CHE...

Страница 58: ...e PULL 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...

Страница 59: ...o manually adjust the brightness of a G500 TXi use the MFD touch screen to change into menu Home than System and into Backlight 3 Annunciator panel PRESS TEST and check that the ALT1 ALT2 ENG YELLOW a...

Страница 60: ...TCH 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 Carb...

Страница 61: ...nd lower RPM second CAUTION 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 WIDE OPEN 2 Propeller control...

Страница 62: ...witch if installed AS REQUIRED OFF AT OAT 59 F 15 C 7 Engine instruments CHECK if in GREEN range 8 Carburetor temperature indicator if installed MONITOR CAUTION Illumination of the red ENG warning due...

Страница 63: ...N as required 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 Th...

Страница 64: ...pment OFF 8 ALT1 BAT switch OFF NOTE The GARMIN G500 G500 TXi 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 Sec...

Страница 65: ...Wing 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 p...

Страница 66: ...POH AFM AQUILA AT01 100C Section 4 NORMAL PROCEDURES Document Nr Issue Supersedes Issue Date Page FM AT01 1010 103 A 08 A 06 01 06 2018 25 05 2020 4 20 intentionally left blank...

Страница 67: ...RAFT 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...

Страница 68: ...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 regul...

Страница 69: ...ge 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 Lev...

Страница 70: ...he 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...

Страница 71: ...POH AFM AQUILA AT01 100C Section 6 WEIGHT AND BALANCE Document Nr Issue Supersedes Issue Date Page FM AT01 1010 103 A 08 A 02 15 10 2013 25 05 2020 6 5 Replace with current Aircraft Weighing Report...

Страница 72: ...d 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 si...

Страница 73: ...oved 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...

Страница 74: ...be 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 1...

Страница 75: ...53 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...

Страница 76: ...0 570 580 590 600 610 620 630 640 650 660 670 680 690 700 710 720 730 740 750 760 230 240 250 260 270 280 290 300 310 320 330 340 350 360 370 380 390 400 410 420 1665 1810 1950 2100 2240 2380 2530 268...

Страница 77: ...l 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 sho...

Страница 78: ...tive 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 prov...

Страница 79: ...5 10 2013 25 05 2020 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 ap...

Страница 80: ...01 1010 103 A 08 A 02 15 10 2013 25 05 2020 6 14 AQUILA AT01 100 Registration S N AT01 100C Designation Description Manufacturer Model P N S N Installation Location Mark where applicable Describe inst...

Страница 81: ...5 7 3 FUSELAGE 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 INSTRU...

Страница 82: ...Fuel 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...

Страница 83: ...e 2 displays the PFD and the MFD Together they form the 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...

Страница 84: ...he ALT1 BAT switch has been turned on 7 1 2 Glass Panel Engine Monitor MVP 50P AQ The MVP 50P AQ consists of an indication actuation interface MVP 50 an engine data converter ECD 33 and the attached p...

Страница 85: ...in 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...

Страница 86: ...trim 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 Adjustab...

Страница 87: ...sted 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 sele...

Страница 88: ...on No Description 1 GARMIN G500 G500 TXi 5 Fuel Pump 9 Landing Light 13 Reserved 17 ELT 21 Glass Panel Engine Monitor MVP 50P AQ 2 Not Occupied 6 Avionics 10 Instrument Lights opt 14 Flap Control Swit...

Страница 89: ...ol 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 windsh...

Страница 90: ...GE 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...

Страница 91: ...ics 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...

Страница 92: ...AT01 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 a...

Страница 93: ...d propeller 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...

Страница 94: ...on 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 prop...

Страница 95: ...uretor 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...

Страница 96: ...e 9 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...

Страница 97: ...P 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 electr...

Страница 98: ...p 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 de...

Страница 99: ...LT1 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 th...

Страница 100: ...ot s Operating Handbook AQUILA AT01 100C Section 7 AIRCRAFT DESCRIPTION Document Nr Issue Supersedes Issue Date Page FM AT01 1010 103 A 08 A 06 01 06 2018 25 05 2020 7 20 Fig Electrical System Schemat...

Страница 101: ...harge discharge 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 Estima...

Страница 102: ...n the 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 ligh...

Страница 103: ...sure 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...

Страница 104: ...fore 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...

Страница 105: ...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 106: ...GTX 330 328 AS 09 Garmin GTN 650 AS 10 Garmin GMA 350 c AS 11 ELT Kannad 406 AS 12 Garrecht TRX 1500 AS 13 Garrecht TRX 2000 AS 14 Trig TT22 AS 15 Garmin SL 30 AS 16 ADF KR 87 AS 17 Garmin GTR 225 225...

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