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Aquila A212 GX Pilot Operating Handbook

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PILOT'S OPERATING HANDBOOK
Type / Model:
Serial Number:
Registration:
Document Number:
First Issue:
Certified according to:
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.
AQUILA A212 GX
AQUILA AT01-200
AT01-200C-
FM-AT01-1010-106
02.03.2020
JAR-VLA

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  • Page 1 PILOT’S OPERATING HANDBOOK AQUILA A212 GX Type / Model: AQUILA AT01-200 Serial Number: AT01-200C- Registration: Document Number: FM-AT01-1010-106 First Issue: 02.03.2020 Certified according to: JAR-VLA This Pilot's Operating Handbook (POH) must be carried on board the aircraft at all times.
  • Page 2 AQUILA AT01-200C INTRODUCTION With the AQUILA AT01 you have acquired a very efficient training and utility aircraft, which is easy to operate and exhibits excellent handling qualities. To ensure reliable operation and trouble free flight, we recommend that you read this Pilot's Operating Handbook thoroughly and adhere to the operating instructions and recommendations given herein.

  • Page 3: Table Of Contents

    Section 0 AQUILA AT01-200C TABLE OF CONTENTS SECTION GENERAL OPERATING LIMITATIONS (approved section) EMERGENCY PROCEDURES (approved section) NORMAL PROCEDURES (approved section) PERFORMANCE (partly approved section) WEIGHT AND BALANCE AIRCRAFT DESCRIPTION HANDLING AND MAINTENANCE SUPPLEMENTS Document Nr.: Issue: Supersedes Issue: Date:...
  • Page 4 Section 0 AQUILA AT01-200C LIST OF EFFECTIVE PAGES Note: If the applicable POH supplement for Night VFR operation is implemented, the list of resulting effective chapters can be found in chapter 9. Section Issue Approved Page Date A.01 0-1 to 0-6 02.03.2020...
  • Page 5 Generally only complete sections of the POH will be exchanged and not individual pages. The operation of the AQUILA AT01 is only permitted with a current and up to date POH carried on board. Please refer to the following web page whenever the revision status of your POH is in question.
  • Page 6 Section 0 AQUILA AT01-200C Revision A.01 of POH ref. FM-AT01-1010-106 is approved under the authority of the DOA ref. EASA.21J.025. Document Nr.: Issue: Supersedes Issue: Date: Page: FM-AT01-1010-106 A.01 --- (first issue) 02.03.2020 0 – 5...
  • Page 7 AVAILABILITY OF TECHNICAL PUBLICATIONS To guarantee safe operation and correct maintenance of the AQUILA AT01-200 aircraft, all manuals and technical publications must be kept in the current effective status. All manuals and technical publications are available from the companies listed below:...

  • Page 8: General

    1.4.1 Overall Dimensions 1.4.2 Wings 1.4.3 Horizontal Stabilizer / Elevator 1.4.4 Fuselage and Vertical Stabilizer / Rudder 1.4.5 Landing Gear AQUILA AT01-200 – THREE VIEW DRAWING ENGINE PROPELLER FUEL OIL AND COOLANT 1.9.1 Engine Oil 1.9.2 Engine Coolant 1.10 WEIGHTS 1.11...
  • Page 9 Manual (Document Number MM-AT01-1020-110). AIRCRAFT TYPE CERTIFICATION The aircraft AQUILA AT01 is type-certified in accordance with the certification specifications of the Joint Aviation Requirements for Very Light Aeroplanes (JAR-VLA, including the revision VLA/92/1) by the Luftfahrt-Bundesamt, the National Aviation Authority of Germany.
  • Page 10 Section 1 AQUILA AT01-200C GENERAL WARNING, CAUTIONS AND NOTES Throughout the text, special text boxes marked WARNING, CAUTION and NOTE are used. These terms are defined as follows: WARNING Procedures, practices, etc. which may result in personal injury or loss of life if not strictly adhered to.
  • Page 11 Section 1 AQUILA AT01-200C GENERAL PRINCIPLE AIRCRAFT DIMENSIONS 1.4.1 Overall Dimensions Wing Span: 33.79 ft (10.30 m) Length: 24.28 ft (7.40 m) Height: 7.87 ft (2.40 m) 1.4.2 Wings Airfoil: HQ-XX mod. Area: 113.02 sq. ft (10.50 m²) Aspect Ratio: 10.10...
  • Page 12 Section 1 AQUILA AT01-200C GENERAL AQUILA AT01-200 – THREE VIEW DRAWING Document Nr.: Issue: Supersedes Issue: Date: Page: FM-AT01-1010-106 A.01 --- (first issue) 02.03.2020 1 - 5...
  • Page 13 Section 1 AQUILA AT01-200C GENERAL ENGINE The ROTAX 914 F3 is a 4-cylinder 4-stroke engine with air cooled cylinders and liquid cooled ® cylinder heads. The Propeller is driven via an internal reduction gearbox with an integrated overload clutch and a hydraulic constant speed propeller governor.
  • Page 14 Section 1 AQUILA AT01-200C GENERAL ENGINE OIL AND COOLANT 1.9.1 Engine Oil Use only oil with an API classification of “SG” or higher. Heavy duty 4-stroke motor oils tend to meet these requirements. For more information regarding engine oil selection, please refer to the Operator’s Manual for all versions of the 914 engine series and to the current issue of the...
  • Page 15 Section 1 AQUILA AT01-200C GENERAL 1.9.2 Engine Coolant A conventional, ethylene glycol and water based coolant is used. Please refer to the Operator’s Manual for the 914 engine series, section 2.2, and to the current issue of the ROTAX Service Instructions SI-914-019 when choosing an engine coolant.
  • Page 16 Section 1 AQUILA AT01-200C GENERAL 1.11 TERMINOLOGY AND ABBREVIATIONS 1.11.1 Speeds IAS: (Indicated Airspeed) - the speed shown on the airspeed indicator KIAS: IAS expressed in knots CAS: (Calibrated Airspeed) - the indicated airspeed, corrected for position and instrument error. CAS is equal to true airspeed in standard atmosphere conditions at sea level.
  • Page 17 Section 1 AQUILA AT01-200C GENERAL 1.11.2 Weight and Balance Reference Datum: imaginary vertical plane from which horizontal distances are measured for balance purposes Reference Line: fixed horizontal reference line Lever Arm: The horizontal distance from the reference datum to the center of gravity (C.G.) of an item...
  • Page 18 Section 1 AQUILA AT01-200C GENERAL 1.11.4 Engine and Performance TOP: (Take-off Power) - maximum power permissible for takeoff MCP: (Max. Continuous Power) - maximum power permitted for continuous operation 1.11.5 Various Serial No. (S/N): Serial Number of the Aircraft Part No. (P/N):...
  • Page 19 Section 1 AQUILA AT01-200C GENERAL 1.12 CONVERSION FACTORS 1.12.1 Length 1 ft 0.304 1 in 25.4 1.12.2 Speed 1 kt 1.852 km/h 1 mph 1.609 km/h 1.12.3 Pressure 1 hPa N/m² 1 mbar 1 in. Hg 33.865 1 psi 68.97 mbar 1.12.4...
  • Page 20 Section 2 AQUILA AT01-200C LIMITATIONS SECTION 2 LIMITATIONS Page INTRODUCTION AIRSPEED LIMITATIONS AIRSPEED INDICATOR MARKINGS POWER PLANT LIMITATIONS 2.4.1 Engine 2.4.2 Propeller MARKINGS ON THE GLASS PANEL ENGINE MONITOR MVP-50P-AQ WEIGHT LIMITS CENTER OF GRAVITY LIMITS MANEUVER LIMITS FLIGHT LOAD FACTORS 2.10...
  • Page 21 Section 2 AQUILA AT01-200C LIMITATIONS INTRODUCTION This section includes all operating limitations, instrument markings and basic placards necessary for the safe operation of the aircraft, its engine, standard systems and standard equipment. WARNING The aircraft must be operated in compliance with the operating limitations.
  • Page 22 Section 2 AQUILA AT01-200C LIMITATIONS AIRSPEED INDICATOR MARKINGS The airspeeds given below are expressed in Indicated Airspeeds (IAS): Marking (IAS) [kts] Remarks White arc Full flap operating range 39-90 Green arc Normal operating range 49-130 Operations in this region must be conducted with...
  • Page 23 Section 2 AQUILA AT01-200C LIMITATIONS Oil Pressure Minimum: 11.6 psi (0.8 bar) below 590 RPM Normal: 29 –72.5 psi (2.0-5.0 bar) above 590 RPM Maximum during a cold start: 101.5 psi (7.0 bar) (only for a short time) Fuel Pressure* Minimum: 2.2 psi...
  • Page 24 Section 2 AQUILA AT01-200C LIMITATIONS 2.5 MARKINGS ON THE ENGINE MONITOR MVP-50P-AQ The following table shows the instrument markings shown on the MVP-50P-AQ and their meaning. Green Arc Red Line Yellow Arc Red Line (normal MVP-50P-AQ (minimum) (caution) (maximum) operating range) Tachometer 535 –...
  • Page 25 Section 2 AQUILA AT01-200C LIMITATIONS WEIGHT LIMITS Maximum Takeoff Weight 1653 lb (750 kg) Maximum Landing Weight 1653 lb (750 kg) Max. Weight in Baggage Compartment 88.2 lb ( 40 kg) WARNING Exceeding the weight limits can overload the aircraft and is prohibited. In addition, aircraft performance and handling characteristics may be detrimentally affected.
  • Page 26 Section 2 AQUILA AT01-200C LIMITATIONS NOTE All acrobatic maneuvers as well as maneuvers with a bank angle exceeding 60° are prohibited. FLIGHT LOAD FACTORS The following flight load factors may not be exceeded while performing any approved maneuvers. Flight Load Factor...
  • Page 27 Section 2 AQUILA AT01-200C LIMITATIONS 2.11 KINDS OF OPERATION LIMITS / MINIMUM EQUIPMENT Certified for: visual flights by Day Table 1 For VFR by Day* • Garmin G500 TXi Flight and navigational instruments • Magnetic Compass • Working timepiece with a seconds hand** •...
  • Page 28 2.14 OPERATING ALTITUDE The Aquila AT01-200 has a maximum operating altitude of 16,400 ft. For flights above FL120 an appropriate oxygen supply for all persons aboard is recommended. Furthermore national regulations have to be considered if applicable.
  • Page 29 Section 2 AQUILA AT01-200C LIMITATIONS 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: Document Nr.:...

  • Page 30: Emergency Procedures (Approved Section)

    SECTION 3 AQUILA AT01-200C EMERGENCY PROCEDURES SECTION 3 EMERGENCY PROCEDURES Page INTRODUCTION 3.1.1 Resetting circuit-breakers AIRSPEEDS FOR EMERGENCY OPERATION ENGINE FAILURES – CHECKLISTS 3.3.1 Engine Failure During the Take-off Run 3.3.2 Engine Failure Immediately After Take-off 3.3.3 In-flight Engine Failure...
  • Page 31 SECTION 3 AQUILA AT01-200C EMERGENCY PROCEDURES 3.11 FLAP CONTROL SYSTEM MALFUNCTIONS 3-20 3.12 TRIM CONTROL SYSTEM FAILURES 3-20 3.12.1 Trim System Inoperative 3-20 3.12.2 Trim Actuator Runaway 3-21 3.13 AVIONICS MALFUNCTIONS 3-21 3.13.1 Complete Avionics Failure 3-21 3.13.2 Receive Mode Failure of COM-Equipment 3-21 3.13.3...
  • Page 32 SECTION 3 AQUILA AT01-200C EMERGENCY PROCEDURES INTRODUCTION This section provides checklists with the recommended procedures for coping with various emergency situations. Emergencies caused by aircraft or engine malfunctions are extremely rare if all pre-flight inspections and required maintenance is properly conducted.
  • Page 33 SECTION 3 AQUILA AT01-200C EMERGENCY PROCEDURES ENGINE FAILURES – CHECKLISTS 3.3.1 Engine Failure before Take-off Throttle IDLE Brakes APPLY as required 3.3.2 Engine Failure Immediately After Take-off and during Climb Airspeed (IAS) 70 KIAS WARNING Depending on the own speed and altitude, the wind condition and the remaining engine power a forced landing must be initiated under consideration of the local conditions.
  • Page 34 SECTION 3 AQUILA AT01-200C EMERGENCY PROCEDURES 3.3.3 In-flight Engine Failures ENGINE ROUGHNESS 1. Carburetor heat PULL (ON) 2. Fuel Pump AUX switch 3. Ignition switch SWITCH through the positions L-BOTH, then R-BOTH 4. Throttle Maintain setting If roughness continues: 5. Throttle REDUCE to min.
  • Page 35 SECTION 3 AQUILA AT01-200C EMERGENCY PROCEDURES SUDDEN LOSS OF MANIFOLD PRESSURE & PROPELLER RPM I. TCU warning light (YELLOW) is NOT blinking - possible Turbocharger defect (loud Bang?) Throttle KEEP manifold pressure in green range Propeller control lever KEEP RPM in green range...
  • Page 36 SECTION 3 AQUILA AT01-200C EMERGENCY PROCEDURES SUDDEN INCREASE OF MANIFOLD PRESSURE & PROPELLER RPM I. TCU warning light (YELLOW) is blinking - waste gate closed Throttle KEEP manifold pressure in green range Propeller control lever KEEP RPM in green range Precautionary landing PERFORM (see 3.4.1)
  • Page 37 SECTION 3 AQUILA AT01-200C EMERGENCY PROCEDURES OSCILLATION OF MANIFOLD PRESSURE & PROPELLER RPM I. TCU warning light (YELLOW) is NOT blinking - Malfunction TCU Throttle middle position (wastegate open) Propeller control lever KEEP RPM in green range TCU switch (Cover up, switch down)
  • Page 38 SECTION 3 AQUILA AT01-200C EMERGENCY PROCEDURES ENGINE RESTART PROCEDURE WITH STOPPED PROPELLER Non-essential electrical equipment ALT1 / BAT switch ALT2 / BAT2 switch Propeller control lever START position Fuel selector valve SWITCH to fullest tank Fuel Pump AUX switch Throttle...
  • Page 39 SECTION 3 AQUILA AT01-200C EMERGENCY PROCEDURES When power is restored: Oil pressure CHECK Choke PUSHED (OFF) Electrical equipment SWITCH ON (as required) Oil temperature CHECK FORCED LANDINGS Generally the flight path should always be chosen such that, in the event of an emergency, a suitable landing field can be reached.
  • Page 40 SECTION 3 AQUILA AT01-200C EMERGENCY PROCEDURES Touch down with lowest possible airspeed. After touchdown: Brakes APPLY as required Fuel selector valve Ignition switch ALT1 / BAT switch ALT2 / BAT2 switch 3.4.2 Emergency Landing NOTE An emergency landing occurs in a state of distress, such as an engine failure, fuel starvation or mechanical problems with the aircraft.
  • Page 41 SECTION 3 AQUILA AT01-200C EMERGENCY PROCEDURES 3.5.2 Engine Fire In-flight Throttle WIDE OPEN Fuel selector valve Cabin heat PUSHED (OFF) Canopy slide-window OPEN Perform a precautionary landing without engine power as described in Section 3.4.2 3.5.3 Electrical Fire with Smoke on the Ground...
  • Page 42 SECTION 3 AQUILA AT01-200C EMERGENCY PROCEDURES INADVERTENT FLIGHT IN ICING CONDITIONS WARNING Intentional flight in icing conditions is prohibited. During unintentional flight in icing conditions proceed as follows: Carburetor heat PULL (ON) Leave icing conditions immediately by flying a reciprocal heading and/or changing...
  • Page 43 SECTION 3 AQUILA AT01-200C EMERGENCY PROCEDURES POWER-OFF GLIDE Achievable gliding distances vary depending on altitude and current wind conditions. This is very important when choosing a landing site or reaching a near-by airfield. To achieve maximum gliding distance: Flaps Airspeed...
  • Page 44 SECTION 3 AQUILA AT01-200C EMERGENCY PROCEDURES 3.10 ELECTRICAL SYSTEM MALFUNCTIONS 3.10.1 Complete Electrical System Failure 1. ALT1 / BAT switch CHECK if ON 2. ALT2 / BAT2 switch CHECK if ON 3. BAT circuit breaker (see 3.1.1) RESET if tripped 4.
  • Page 45 SECTION 3 AQUILA AT01-200C EMERGENCY PROCEDURES 3.10.2 Battery discharges (BAT) Warning light ENG (RED) with ammeter values ALT1 and/or ALT2 shown in RED and thus BAT shown in YELLOW (with or without ALT1 and/or ALT2 warning light is illuminated) If an ammeter value for BAT is shown in YELLOW on the MVP, the power supply of both alternators into the on-board electricity system is insufficient - Battery is discharging.
  • Page 46 SECTION 3 AQUILA AT01-200C EMERGENCY PROCEDURES 3.10.3 Alternator 1 (ALT1) failure Warning light ENG (RED) with ammeter values ALT1 shown in RED and / or ALT1 warning light is illuminated 1. ALT1 switch SWITCH through OFF – ON, approx. 10 sec.
  • Page 47 SECTION 3 AQUILA AT01-200C EMERGENCY PROCEDURES 3.10.4 Alternator 2 (ALT2) failure Warning light ENG (RED) with ammeter values ALT2 shown in RED and / or ALT2 warning light is illuminated 1. Fuel pump AUX switch 2. ALT2 / BAT2 switch check, if ON 3.
  • Page 48 SECTION 3 AQUILA AT01-200C EMERGENCY PROCEDURES 3.10.5 Low Voltage Indication On the ground (voltmeter values YELLOW or RED) Engine speed Increase RPM until value turns GREEN (RPM should be below 1350) All non-essential equipment OFF, until value turns GREEN. If the value remains YELLOW or RED Do not fly before problem is eliminated.

  • Page 49: Flap Control System Malfunctions

    SECTION 3 AQUILA AT01-200C EMERGENCY PROCEDURES 3.11 FLAP CONTROL SYSTEM MALFUNCTIONS FLAP POSITION INDICATOR or FLAP ACTUATOR MALFUNCTION Flap Actuator circuit breaker (see 3.1.1) RESET, if tripped Flap Control circuit breaker (see 3.1.1) RESET, if tripped Flap position visually CONFIRM on the left wing...

  • Page 50: Trim Actuator Runaway

    SECTION 3 AQUILA AT01-200C EMERGENCY PROCEDURES 3.12.2 Trim Actuator Runaway Control Column HOLD in position Elevator Trim circuit breaker PULL Trim switch CHECK if pressed or jammed If the problem is obvious, and can be solved: Elevator Trim circuit breaker (see 3.1.1) RESET NOTE Approx.

  • Page 51: Primary Flight Display Failure

    SECTION 3 AQUILA AT01-200C EMERGENCY PROCEDURES 3.13.4 Primary Flight Display Failure 1. PFD circuit breaker (see 3.1.1) RESET, if tripped It is possible to safely continue flight, even if the PFD failure cannot be corrected in flight, by referencing the remaining instruments. It may, none the less, be prudent to land at the nearest airfield.

  • Page 52: Ahrs Failure

    SECTION 3 AQUILA AT01-200C EMERGENCY PROCEDURES 3.13.7 AHRS Failure 1. Attitude Natural horizon NOTE In the event of an AHRS Failure, the horizon is no longer displayed on the PFD. Additionally a red “X” and in yellow “AHRS FAILURE” is displayed. A Navigation System Failure, as described in section 3.13.6, accompanies an AHRS Failure.

  • Page 53: Starter Malfunction

    SECTION 3 AQUILA AT01-200C EMERGENCY PROCEDURES 3.14 STARTER MALFUNCTION During engine start on ground, power transmission from the starter to the engine is defect (a continuing and excessive howling tone is audible). Throttle IDLE Ignition switch Repair damage before conducting planned flight.

  • Page 54: Normal Procedures (Approved Section)

    Section 4 AQUILA AT01-200C NORMAL PROCEDURES SECTION 4 NORMAL PROCEDURES Page INTRODUCTION AIRSPEEDS FOR NORMAL OPERATION DAILY INSPECTION PRE-FLIGHT INSPECTION CHECKLISTS FOR NORMAL PROCEDURES 4-11 4.5.1 Before Engine Start-up 4-11 4.5.2 Engine Start-up 4-12 4.5.3 Before Taxiing 4-13 4.5.4 Taxiing 4-13 4.5.5...
  • Page 55 Section 4 AQUILA AT01-200C NORMAL PROCEDURES INTRODUCTION This section 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.
  • Page 56 Section 4 AQUILA AT01-200C NORMAL PROCEDURES AIRSPEEDS FOR NORMAL OPERATION The following airspeeds are based on the maximum take-off weight of 1653 lbs (750 kg). They may also be used for any lower operational weight. TAKE-OFF Airspeed (IAS) Normal climb speed to 50 Feet...
  • Page 57 Section 4 AQUILA AT01-200C NORMAL PROCEDURES DAILY INSPECTION CAUTION The daily inspection is begun by checking all 3 fuel sumps for water and contamination. This must be done before the aircraft is moved. Otherwise the fuel in the sump may mix.
  • Page 58 Section 4 AQUILA AT01-200C NORMAL PROCEDURES 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.
  • Page 59 Section 4 AQUILA AT01-200C NORMAL PROCEDURES Left 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)
  • Page 60 Section 4 AQUILA AT01-200C NORMAL PROCEDURES Nose landing gear a) Nose gear strut Visual inspection b) Wheel fairing Visual inspection CAUTION Both parts of the 2 piece nose wheel fairing must always be installed on the aircraft c) Tire pressure and slip marking...
  • Page 61 Section 4 AQUILA AT01-200C NORMAL PROCEDURES b) Check coolant level: Verify coolant level expansion tank replenish required. (The expansion tank must least 2/3 filled or coolant has to be visible at the gauge glass.) Verify coolant level overflow bottle replenish required.
  • Page 62 Section 4 AQUILA AT01-200C NORMAL PROCEDURES PRE-FLIGHT INSPECTION (Walk Around) Daily Inspection Confirm has been carried out. Tow bar Removed? Fuel level CHECK with dipstick and verify with the indicated fuel level on the fuel gauge WARNING Before cranking the propeller: Ignition, ALT1/BAT switch and ALT2/BAT2 switch: OFF Set the parking brake.
  • Page 63 Section 4 AQUILA AT01-200C NORMAL PROCEDURES 6. Tie-down straps remove 7. Baggage door CHECK if closed and locked 8. Pitot cover remove 9. Control locks remove 10. Seating position adjust and lock, check that nose wheel steering and brakes can be operated 11.
  • Page 64 Section 4 AQUILA AT01-200C NORMAL PROCEDURES CHECKLISTS FOR NORMAL PROCEDURES 4.5.1 Before Engine Start-up Daily and Pre-Flight Inspection COMPLETED Passenger Briefing COMPLETED Seats ADJUSTED Seat Belts and Harnesses FASTENED Canopy CLOSED and LOCKED Check locking mechanism Parking Brake SET (pull lever back)
  • Page 65 Section 4 AQUILA AT01-200C NORMAL PROCEDURES 4.5.2 Engine Start-up Fuel Pump AUX switch Fuel Pressure within GREEN range (AUX pump OK) Fuel Pump AUX switch ALT2 / BAT2 switch ALT2 warning light ILLUMINATES Fuel pressure within GREEN range (MAIN pump OK)
  • Page 66 Section 4 AQUILA AT01-200C NORMAL PROCEDURES 4.5.3 Before Taxiing CAUTION Warm up the engine for approx. 2 min at 800 RPM and then at 1000 RPM until the Oil Temperature reaches at least 122°F (50°C) Avionics switch Avionics and flight instruments The GARMIN G500 TXi has an integrated sensor that automatically adjusts the brightness of the display.
  • Page 67 Section 4 AQUILA AT01-200C NORMAL PROCEDURES CAUTION Do not operate the engine at high RPM when taxiing to prevent damage to the propeller through stones or other foreign objects. 4.5.5 Before Take-off (at the Taxi Holding Position) Brakes APPLY and HOLD...
  • Page 68 Section 4 AQUILA AT01-200C NORMAL PROCEDURES 4.5.6 Take-off (up to 50 ft) CAUTION To increase power setting raise RPM first and open throttle second. To decrease power setting close throttle first and lower RPM second. Throttle WIDE OPEN (TOP = 115% MCP)
  • Page 69 Section 4 AQUILA AT01-200C NORMAL PROCEDURES 4.5.8 Cruise Throttle AS REQUIRED (Ref. to Section 5, Page 5-11) Propeller control lever SET 1650 to 2260 RPM CAUTION Continuous operation with throttle wide open and propeller revolution below 2140 RPM should be avoided to prevent engine damage in particular at pressure altitudes below 3000ft and at...
  • Page 70 Section 4 AQUILA AT01-200C NORMAL PROCEDURES 4.5.10 Landing Lap belt CHECK SECURE Fuel Pump AUX switch Carburetor heat PULL (ON) Throttle AS REQUIRED Airspeed 90 KIAS Flaps switch T/O or LDG Trim switch AS REQUIRED Flaps switch Approach speed 60 KIAS...
  • Page 71 Section 4 AQUILA AT01-200C NORMAL PROCEDURES 4.5.13 Engine Shutdown Throttle IDLE Parking Brake Flaps switch CHECK (frequency 121.5 MHz) Avionics switch Engine run with below 1000 RPM min. 2 minutes (incl. taxiing) for turbocharger cool down Ignition Switch ALT2 / BAT2 switch...
  • Page 72 Section 4 AQUILA AT01-200C NORMAL PROCEDURES 4.5.15 Flight in Heavy Rain and/or with 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 performance, cruising speed and stall characteristics.
  • Page 73 Section 4 AQUILA AT01-200C NORMAL PROCEDURES [intentionally left blank] Document Nr.: Issue: Supersedes Issue: Date: Page: FM-AT01-1010-106 A.01 --- (first issue) 02.03.2020 4 - 20...

  • Page 74: Performance (Partly Approved Section)

    Section 5 PERFORMANCE AQUILA AT01-200C SECTION 5 PERFORMANCE Page INTRODUCTION PERFORMANCE CHARTS 5.2.1 Airspeed Calibration 5.2.2 Stall Speeds 5.2.3 Crosswind Component 5.2.4 Flight Planning 5.2.5 Take-off Distance 5.2.6 Climb Performance / Cruise Altitude 5.2.7 Climb: Fuel Consumption, Time and Distance 5.2.8...
  • Page 75 INTRODUCTION The performance data in the following charts give an overview on the performance and capabilities of the AQUILA AT01. This information provides the basis for flight planning prior to every flight. All data in the charts haves been acquired during flight testing conducted with an aircraft and engine in a good operating condition.
  • Page 76 Section 5 PERFORMANCE AQUILA AT01-200C 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 instrument error Example: 120 KIAS (indicated airspeed) corresponds to 118 KCAS (calibrated airspeed)
  • Page 77 Section 5 PERFORMANCE AQUILA AT01-200C 5.2.2 Stall Speeds Stall speeds were determined in the following configuration: Forward center of gravity (CG) limit: 16.8 in (427 mm) behind the Ref. Datum Takeoff mass 1653 lb. (750 kg) Engine idle Bank Angle Flap 0°...
  • Page 78 Section 5 PERFORMANCE AQUILA AT01-200C 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] Document Nr.: Issue: Supersedes Issue: Date: Page: FM-AT01-1010-106 A.01 --- (first issue) 02.03.2020...
  • Page 79 Section 5 PERFORMANCE AQUILA AT01-200C 5.2.4 Flight Planning The performance tables and diagrams on the following pages contain all information required for flight planning from take-off at your point of departure to the landing at your destination. Experience shows that the data determined during flight planning match the values achieved in flight accurately.
  • Page 80 Section 5 AQUILA AT01-200C PERFORMANCE 5.2.5 Take-off Distance Notes: Take-off Mass [lbs] Airspeed [KIAS] ([kg]) [ft] Lift-off 50 ft - 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...
  • Page 81 Section 5 AQUILA AT01-200C PERFORMANCE 5.2.6 Rate of Climb / Cruise Altitude Mass [lbs] 1720 1670 1620 1570 1520 1470 1420 1370 1320 Take-off Mass [lbs] Best Rate-of-Climb Speed [KIAS] 1400 Service Ceiling (ISA) ([kg]) MSL-5000 ft bis 10 000ft...
  • Page 82 Section 5 AQUILA AT01-200C PERFORMANCE 5.2.7 Climb: Fuel, Time and Distance Conditions: Time, distance and fuel: Vy= 66 KIAS, up to 5000 ft For each 8°C above ISA, increase 2260 rpm, MCP, 750 kg (1654 lbs): decrease by 15% Vy= 64 KIAS, up to 10.000 ft time, distance and fuel by 10%.
  • Page 83 Section 5 AQUILA AT01-200C PERFORMANCE 5.2.8 Cruising Speed (TAS − True airspeed) Notice: Flying without any wheel fairings or with mud guards reduces Conditions: Power Setting: according to page 5-11 performence up to 10%. Flaps: UP Outside Air Temperature [°F]...
  • Page 84 Section 5 AQUILA AT01-200C PERFORMANCE 5.2.9 Cruise Power Settings Engine performance in % of the maximum continuous power Pressure Standard Altitude Temp. [ft] [°C] [°F] [U/min] [in Hg] [l/h] [gal/h] [U/min] [in Hg] [l/h] [gal/h] [U/min] [in Hg] [l/h] [gal/h] [U/min] [in Hg] [l/h] [gal/h] [U/min] [in Hg] [l/h] [gal/h] 1770 13.5...
  • Page 85 Section 5 PERFORMANCE AQUILA AT01-200C 5.2.10 Maximum Endurance Conditions: Notice: Fuel quantity: usable fuel 28.9 US gal (109,6 l) Power Setting: according to page 5-11 A not properly maintained engine The calculation of the endurance includes: Flaps: UP and aircraft may considerably 1.
  • Page 86 Section 5 PERFORMANCE AQUILA AT01-200C 5.2.11 Maximum Range Conditions: Notice: Fuel quantity: usable fuel 28.9 US gal (109,6 l) Power Setting: according to page 5-11 A not properly maintained engine The calculation of the endurance includes: Flaps: UP and aircraft may considerably 1.
  • Page 87 Section 5 AQUILA AT01-200C PERFORMANCE 5.2.12 Descent: Fuel, Time, Distance Procedure: Conditions: In descent follow a speed of 121 KIAS. Manifold Pressure: as required. Approx. 15 inHg Set performance for a descent rate of 750 ft / min. Prop speed: 2000 rpm Keep the engine temperature in the green range.
  • Page 88 Section 5 AQUILA AT01-200C PERFORMANCE 5.2.13 Landing Distance Notice: Airspeed [KIAS] Landing Mass [lbs] - When landing on a dry, mown grass runway, increase the required landing distances by 15%. ([kg]) in 50 ft Touchdown - Increase ground roll appropriately for wet grass / ground, ice, snow and slush.
  • Page 89 Section 5 AQUILA AT01-200C PERFORMANCE 5.2.14 Climb Performance after Balked Landing Conditions: Take-off Mass [lbs] ([kg]) Airspeed [KIAS] Mass ([bs] Power Setting: full throttle 1764 (800) 1720 1670 1620 1570 1520 1470 1420 1370 1320 1000 Prop Speed: 2385 rpm...
  • Page 90 Section 5 PERFORMANCE AQUILA AT01-200C 5.2.15 Flight Planning Example The following contains a flight-planning example to demonstrate the use of the tables, charts and data presented in this section of the POH. The flight planning is based upon the following...
  • Page 91 Section 5 PERFORMANCE AQUILA AT01-200C We now have all the necessary data to determine the required take-off distances from chart 5.2.5: Take-off ground roll.........210 m Lift-off speed...........50 KIAS Take-off distance over a 50 ft obstacle...375 m Airspeed in 50 ft..........57 KIAS The required take-off distance is less than the available runway length (TODA) of 620m.
  • Page 92 Section 5 PERFORMANCE AQUILA AT01-200C CRUISE Cruise altitude is chosen under consideration of flight distance, en-route winds and aircraft performance. In this flight-planning example, a typical cruise altitude and en-route wind condition has been chosen. The range diagram 5.2.11 on page 5-13 shows the relationship between the engine power setting and the maximum achievable range.
  • Page 93 Section 5 PERFORMANCE AQUILA AT01-200C CALCULATION OF FUEL REQUIRED Fuel required for engine start-up and taxiing 0.8 US gal (3.0 ltr) (General Value, see remark “Fuel Quantity” on pg. 5-12 and 5-13) Fuel required for climb (page 5-18) +1.25 US gal (4.7 ltr) 2.05 US gal (7.7 ltr)
  • Page 94 Section 5 PERFORMANCE AQUILA AT01-200C The total amount of fuel required is calculated as follows: Engine start-up, taxiing and climb 2.04 US gal (7.7 ltr) Cruise 19.14 US gal (72.45 ltr) Descent 0.44 US gal (1.65 ltr) Total fuel required 21.62 US gal (81.8 ltr)
  • Page 95 Section 5 PERFORMANCE AQUILA AT01-200C CLIMB PERFORMANCE AFTER BALKED LANDING In order to determine the possible climb performance after a balked landing use chart 5.2.14 on page 5-16. A climb performance of 822 ft/min is determined for an aircraft mass of 1500 lbs (680 kg) at a pressure altitude of 380 ft and an outside air temperature of 68 °F (20°C).
  • Page 96 Section 5 PERFORMANCE AQUILA AT01-200C NOISE CHARACTERISTICS / ABATEMENT Actual Certification basis Maximum Allowable (MTOW: 750kg / 1653 lbs) 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) Document Nr.: Issue: Supersedes Issue:...
  • Page 97 Section 5 PERFORMANCE AQUILA AT01-200C [intentionally left blank] Document Nr.: Issue: Supersedes Issue: Date: Page: FM-AT01-1010-106 A.01 --- (first issue) 02.03.2020 5 - 24...

  • Page 98: Weight And Balance

    Section 6 AQUILA AT01-200C WEIGHT AND BALANCE SECTION 6 WEIGHT AND BALANCE / EQUIPMENT LIST Page INTRODUCTION AIRCRAFT WEIGHING WEIGHT AND BALANCE DATA 6.3.1 Weight and Balance Record DETERMINING WEIGHT AND BALANCE FOR FLIGHT 6.4.1 Load moment determination (loading graph) 6.4.2...
  • Page 99 Section 6 AQUILA AT01-200C WEIGHT AND BALANCE INTRODUCTION Before delivery, the manufacturer determines the basic empty weight and moment as well as the empty C.G. location for each aircraft. This data is documented in the Weight and Balance Record in section 6.3.1 of this section. The certified empty C.G. limits can be found in the Maintenance Manual.
  • Page 100 Section 6 AQUILA AT01-200C WEIGHT AND BALANCE AIRCRAFT WEIGHING Reference Datum (BE): Leading edge of wing root rib Horizontal reference line: Place a wedge (800 : 77) 63 in (1600 mm) ahead of the leading edge of the horizontal stabilizer. Place a level on the wedge and level the aircraft.
  • Page 101 Section 6 AQUILA AT01-200C WEIGHT AND BALANCE Aircraft Weighing: Example in [lb, in] Position Weight [lb] * Lever [in] = Moment [in*lb] Nose Wheel = 234 = - 33 = - 7722 Left Main Wheel = 441 = + 31...
  • Page 102 Section 6 AQUILA AT01-200C WEIGHT AND BALANCE Replace with current Aircraft Weighing Report Document Nr.: Issue: Supersedes Issue: Date: Page: FM-AT01-1010-106 A.01 --- (first issue) 02.03.2020 6 - 5...
  • Page 103 Section 6 AQUILA AT01-200C WEIGHT AND BALANCE 6.3.1 Weight and Balance Record Document Nr.: Issue: Supersedes Issue: Date: Page: FM-AT01-1010-106 A.01 --- (first issue) 02.03.2020 6 - 6...
  • Page 104 Section 6 AQUILA AT01-200C WEIGHT AND BALANCE DETERMINING WEIGHT AND BALANCE FOR FLIGHT In order to operate the aircraft within the approved weight and C.G. limits, the take-off weight and the flight C.G. position must be determined, taking into consideration the loading for the planned flight.
  • Page 105 Section 6 AQUILA AT01-200C WEIGHT AND BALANCE 6.4.1 Load moment determination (loading graph) Loading Graph Seat most Seat most forward rearward Kraftstoff fuel baggage Gepäck 940 1010 Moment of loading [kg m] ([lb ft]) NOTE When determining the C.G. position, the fact that the seat is adjustable must be taken into consideration.
  • Page 106 Section 6 AQUILA AT01-200C WEIGHT AND BALANCE 6.4.2 Weight and Moment Determination Registration No.: Aquila AT01 Lever from leading Example Calculating edge of wing root Loading Weight Moment Weight Moment rib (BE) Condition [lb] [in lb] [lb] [in lb] [in] [m]...
  • Page 107 Section 6 WEIGHT AND BALANCE AQUILA AT01-200C 6.4.3 Approved Center of Gravity Range and Moment Limits xS =16.8 in 17.1 17.9 18.7 19.5 20.3 xS = 20.6 in xS = 427mm xS = 523 mm 1675 1650 1630 1610 1585...
  • Page 108 Section 6 AQUILA AT01-200C WEIGHT AND BALANCE 6.4.4 Estimating Center of Gravity Position using MVP-50P-AQ The "Weight and Balance" function of the MVP-50P-AQ offers a comfortable and simple way of estimating the current C.G. position. The weights of the pilot, passenger, baggage and fuel are entered into the "Weight and Balance"...
  • Page 109 Service Bulletin. When in doubt, the type certificate holder or the production organization of AQUILA Aviation should be contacted. After every change to the aircraft that could cause the empty weight or moment to change (for example, the installation or removal of equipment), the empty weight and C.G.
  • Page 110 Section 6 AQUILA AT01-200C WEIGHT AND BALANCE 6.5.1 Current Equipment List of the Aircraft AQUILA AT01-200 Registration: S/N: AT01-200C- Installation Designation / Description Manufacturer Model / P/N Location **) Mark where applicable Describe installation location or enter lever arm from reference datum in [in] (keep algebraic sign of lever arm in mind) Document Nr.:...
  • Page 111 Section 6 AQUILA AT01-200C WEIGHT AND BALANCE AQUILA AT01-200 Registration: S/N: AT01-200C- Installation Designation / Description Manufacturer Model / P/N Location **) Mark where applicable Describe installation location or enter lever arm from reference datum in [in] (keep algebraic sign of lever arm in mind) Document Nr.:...

  • Page 112: Aircraft Description

    Section 7 AQUILA AT01-200C AIRCRAFT DESCRIPTION SECTION 7 DESCRIPTION OF THE AIRCRAFT AND ITS SYSTEMS Page INTRODUCTION 7.1.1 Garmin G500 TXi System (Primary Flight Display) 7.1.2 Glass Panel Engine Monitor MVP-50P-AQ AIRFRAME FUSELAGE WING EMPENNAGE FLIGHT CONTROLS 7.6.1 Ailerons 7.6.2 Elevator and Trim System 7.6.3...
  • Page 113 Section 7 AQUILA AT01-200C AIRCRAFT DESCRIPTION 7.12 POWER PLANT 7-13 7.12.1 Engine 7-13 7.12.2 Propeller 7-13 7.12.3 Throttle and Propeller Control 7-14 7.12.4 Choke 7-15 7.12.5 Carburetor Heat 7-15 7.13 FUEL SYSTEM 7-16 7.13.1 Overview 7-16 7.13.2 Fuel Tank 7-17 7.13.3...
  • Page 114 Section 7 AQUILA AT01-200C AIRCRAFT DESCRIPTION INTRODUCTION Section 7 of the Pilot's Operating Handbook contains a description of the entire aircraft and its systems, including the integration of the GARMIN G500 TXi system and the Glass Panel Engine Monitor MVP-50P-AQ as well as information related to their use.
  • Page 115 Section 7 AQUILA AT01-200C AIRCRAFT DESCRIPTION 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 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).
  • Page 116 The Aquila AT01-200 is a modern single engine two seater in a side-by-side configuration. Due to its high useful load, roomy cockpit, large baggage compartment, good cruise performance and light yet incredibly sturdy airframe, the Aquila is not only a great aircraft for longer tours but also an ideal training platform.
  • Page 117 AQUILA AT01-200C AIRCRAFT DESCRIPTION FLIGHT CONTROLS The flight controls of the Aquila AT01-200 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.
  • Page 118 Section 7 AQUILA AT01-200C AIRCRAFT DESCRIPTION 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 selector switch is incorporated in the instrument panel for flap operation. A flap position indicator is also located on the instrument panel.
  • Page 119 Section 7 AIRCRAFT DESCRIPTION AQUILA AT01-200C NOTE: INSTRUMENT PANEL AT01-200C (sample) actual installation differ depending certified changes complementary equipment. For minimum instrument requirements, refer to Section 2.12 of this manual No. Description No. Description No. Description Description No. Description No. Description...
  • Page 120 Section 7 AIRCRAFT DESCRIPTION AQUILA AT01-200C 7.7.1 Overview Control Panel Controls and displays located on the control panel which is located below the midsection of the instrument panel, are placed so as to be easily viewed and operated from both seats.
  • Page 121 BAGGAGE COMPARTMENT The AQUILA AT01-200 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 cabin.
  • Page 122 Because of the robust landing gear and 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.
  • Page 123 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 left and right main wheels have the same fairing.

  • Page 124: Power Plant

    Section 7 AIRCRAFT DESCRIPTION AQUILA AT01-200C 7.12 POWER PLANT 7.12.1 Engine The ROTAX 914F is a 4 cylinder, 4 stroke horizontally opposed engine with liquid- cooled cylinder heads and air-cooled cylinder barrels. It has brushless magnetos, 2 carburetors, 2 electrical fuel pumps, a reduction drive, an integrated alternator (ALT2), an externally engine mounted alternator (ALT1) and an attachment for a hydraulic constant speed propeller.

  • Page 125: Throttle And Propeller Control

    Section 7 AIRCRAFT DESCRIPTION AQUILA AT01-200C 7.12.3 Throttle and Propeller Control The black throttle lever and the blue propeller control lever are located on the central control panel. The throttle controls the manifold pressure (MP): Throttle forward, more than 100% indexed position: Take-off power (TOP)

  • Page 126: Choke

    Section 7 AIRCRAFT DESCRIPTION AQUILA AT01-200C 7.12.4 Choke The choke control knob is located on the control panel to the right of the carburetor heat and cabin heat controls. The choke may only be used for a short time when starting the engine in cold conditions.

  • Page 127: Fuel System

    Section 7 AIRCRAFT DESCRIPTION AQUILA AT01-200C 7.13 FUEL SYSTEM 7.13.1 Overview right wing tank right wing tank left wing tank left wing tank MVP50P Fuel supply line Fuel return line Fuel Vent Airbox pressure probe Drain valve Glass Panel Engine Monitor...

  • Page 128: Fuel Tank

    Section 7 AIRCRAFT DESCRIPTION AQUILA AT01-200C 7.13.2 Fuel Tank Each wing is equipped with an integral fuel tank. The fuel line of each tank is equipped with a removable coarse fuel filter. The fuel filler caps can be locked. A drain valve is located at the lowest point of each fuel tank. Another drain valve is in the gascolator located behind the firewall on the co-pilots side.

  • Page 129: Fuel Level Indication

    Section 7 AIRCRAFT DESCRIPTION AQUILA AT01-200C When the fuel selector valve is in the OFF position, the fuel flow in the supply and return lines is interrupted and it functions as a fuel shut-off valve. To switch the valve into the OFF-position, the knob located at the top of the handle must be PULLED while simultaneously turning the handle clockwise into the OFF-position.

  • Page 130: Electrical System

    Section 7 AIRCRAFT DESCRIPTION AQUILA AT01-200C 7.14 ELECTRICAL SYSTEM The AT01-200 is equipped with a 12 V direct current (DC) electrical system that is powered by 2 engine-driven alternators and a battery. When the two ALT1 / BAT and ALT2 / BAT2 split master switches are engaged, the electrical equipment can be operated and controlled by rocker switches located on the lower left section of the instrument panel.
  • Page 131 Section 7 AIRCRAFT DESCRIPTION AQUILA AT01-200C Fig.: Electrical System Schematic 1/2 Document Nr.: Issue: Supersedes Issue: Date: Page: FM-AT01-1010-106 A.01 --- (first issue) 02.03.2020 7 - 20...
  • Page 132 Section 7 AIRCRAFT DESCRIPTION AQUILA AT01-200C Fig.: Electrical System Schematic 2/2 Document Nr.: Issue: Supersedes Issue: Date: Page: FM-AT01-1010-106 A.01 --- (first issue) 02.03.2020 7 - 21...

  • Page 133: Electrical Equipment And Circuit Breakers

    Section 7 AIRCRAFT DESCRIPTION AQUILA AT01-200C 7.14.3 Electrical Equipment and Circuit Breakers All electrical equipment can be turned on or off by push-pull type circuit breakers or by rocker switches with built-in circuit breaker function. COM/NAV-equipment along with other avionic equipment is supplied with electrical power through the Avionics switch.

  • Page 134: Voltmeter And Amperemeter

    Section 7 AIRCRAFT DESCRIPTION AQUILA AT01-200C If a yellow or red range is reached, the affected data or value will blink in the appropriate color. In addition, the yellow or red ENG warning light in the annunciator panel will illuminate. In the case of a YELLOW warning light, the blinking can be stopped and the alarm confirmed by pressing any switch on the MVP-50P-AQ.

  • Page 135: Warning Light Boost

    Section 7 AIRCRAFT DESCRIPTION AQUILA AT01-200C 7.16.3 Warning Light TCU The yellow TCU warning light should not illuminate during normal operation. The YELLOW warning light flashes only if: • TCU, turbocharger or waste gate malfunction occurs In case of a TCU malfunction the connection between TCU and servo motor can be interrupted by switching TCU switch OFF (switched down).

  • Page 136: External Power Unit

    Section 7 AIRCRAFT DESCRIPTION AQUILA AT01-200C 7.17 EXTERNAL POWER UNIT (optional) It is recommended to use an External Power Unit (EPU) for engine start-up at outside air temperatures below –10° C. The EPU receptacle is optional and is mounted on the right fuselage side below the battery.

  • Page 137: Pitot Heat

    Section 7 AIRCRAFT DESCRIPTION AQUILA AT01-200C 7.18.1 Pitot Heat (optional) On request, a heated pitot-static tube can be installed. The heater is turned on using the P/S Heat switch. The size and location of the heated pitot static tube are identical to the unheated version.
  • Page 138 Section 8 AQUILA AT01-200C HANDLING & MAINTENANCE SECTION 8 HANDLING, SERVICE & MAINTENANCE Page INTRODUCTION AIRCRAFT INSPECTION PERIODS MODIFICATIONS AND REPAIRS GROUND HANDLING 8.4.1 Towing 8.4.2 Parking 8.4.3 Tie-Down 8.4.4 Jacking CLEANING AND CARE 8.5.1 Painted Surfaces 8.5.2 Canopy 8.5.3 Propeller 8.5.4...
  • Page 139 Section 8 AQUILA AT01-200C HANDLING & MAINTENANCE INTRODUCTION Section 8 contains factory recommended procedures for correct ground handling as well as information regarding care and servicing of the aircraft. Furthermore, it includes requirements which must be adhered to during inspection as well as during maintenance and when modifications and repairs are carried out.
  • Page 140 Section 8 AQUILA AT01-200C HANDLING & MAINTENANCE GROUND HANDLING 8.4.1 Towing 8.4.1.1 Moving forwards The aircraft can be safely moved and controlled by one person on a smooth and level surface with the tow bar attached to the nose wheel.
  • Page 141 Section 8 AQUILA AT01-200C HANDLING & MAINTENANCE CAUTION Temperatures higher than 50°C in the cockpit may damage avionics and instruments. When parked in the sun, use a canopy cover to keep the cockpit cool. 8.4.3 Tie-Down The aircraft has three tie-down points; two are located on the lower surface of the wings in the outboard section (fitted with M 8 threads) and the third is located on the lower fin.
  • Page 142 8.5.1 Painted Surfaces To maintain the excellent flight performance and handling qualities of the AQUILA AT01-200 the aircraft must be kept clean and free of damage. Therefore it is recommended to regularly clean the aircraft, paying close attention to the leading edges of the wings and stabilizers.
  • Page 143 Section 8 AQUILA AT01-200C HANDLING & MAINTENANCE 8.5.2 Canopy Since acrylic glass can be easily scratched, the same principles apply as for cleaning painted surfaces. The canopy should be cleaned using plenty of water, a soft clean sponge and chamois leather.
  • Page 144 If modifications requiring an STC have been conducted on your aircraft at a Maintenance Organization other than AQUILA Aviation, it is the owner’s responsibility to ensure that the appropriate supplements are included in this manual and properly recorded in the index of supplements in section 9.2.
  • Page 145 Garmin G5 Stby AI AS-22 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.de) via dedicated Service Information (SI). Document Nr.: Issue: Supersedes Issue:...

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