Aquila AT01 User manual

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AQUILA AT01-100A Section 0
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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.
CAUTION
All limitations, procedures and performance data contained in this handbook are EASA/FAA
approved and mandatory. Failing to follow the procedures and limits set forth in this handbook
can lead to a loss of liability by the manufacturer.
THE HANDBOOK
The handbook is 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
Contents is located at the beginning of each section to aid the location of specific data within
that section.
All rights reserved.
Reproduction or disclosure to third parties of this document or any part thereof is not permitted,
except with the prior and express written permission of AQUILA Aviation International GmbH.
Copyright © by Aviation International GmbH
Schönhagen, Germany

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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 AND SYSTEMS DESCRIPTION 7
HANDLING AND MAINTENANCE 8
SUPPLEMENTS 9

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LIST OF EFFECTIVE PAGES
Section
Issue
Approved
Page
Date
0 A.05 0-1 to 0-6 26.06.2017
1 A.02 1-1 to 1-12 15.10.2013
2 A.05 X 2-1 to 2-10 26.06.2017
3 A.05 X 3-1 to 3-16 26.06.2017
4 A.04 X 4-1 to 4-18 19.10.2015
5 A.05 (X)* 5-1 to 5-22 26.06.2017
6 A.02 6-1 to 6-14 15.10.2013
7 A.05 7-1 to 7-22 26.06.2017
8 A.02 8-1 to 8-6 15.10.2013
9 A.05 9-1 to 9-2 26.06.2017
* - partially approved

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LIST OF REVISIONS
All revisions to the handbook, with the exception of individual weight and balance data and
revisions to the Equipment List, must be recorded in the List of Revisions. Revisions must
either be approved by EASA or, in the case of changes, in accordance with Part 21A.263(c)(4)
by the Design Organization of AQUILA Aviation International GmbH.
Additions and revisions to text in 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 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.
www.aquila-aviation.de
Issue Description of
Revision Revised Section(s)
EASA
Approval-
number
Approval by
AQUILA / EASA
Date / Signature
A.01 First Issue All 10045112 29.05.2013
A.02 Editorial changes, Supplements 8,33 kHz
FAA certification All 15.10.2013
A.03 AS-00 „Winter
Operation“ 0, 9 08.04.2014
A.04 Editorial changes 0, 4 19.10.2015
A.05 Minor changes, AS-21 “GTX 335 / 345”, SB-
AT01-029 incorporated
0, 2, 3, 5,
7, 9 26.06.2017

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Revision A.05 of AFM ref. FM-AT01-1010-101 is approved under the authority of DOA ref. EASA.21J.025.

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Reporting of safety / airworthiness relevant occurrences:
Tel: ++49 (0)33731-707-0
Fax: ++49 (0)33731-707-11
E-Mail: [e-mail]
AVAILABILITY OF TECHNICAL PUBLICATIONS
To guarantee safe operation and correct maintenance of the AQUILA AT01-100 aircraft, all
manuals and technical publications must be kept in the current effective status.
All manuals and technical publications relating to the aircraft AQUILA AT01-100 are available
from the companies listed below:
(a) AQUILA AT01-100B 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: [e-mail]
Internet: http://www.aquila-aviation.de
(b) Engine ROTAX 912 S related Manuals and Publications
Contact the ROTAX®authorized distributor for ROTAX®Aircraft Engines of the
applicable distribution area.
For contact details of the local authorized distributor for ROTAX Aircraft Engines,
please refer to chapter 13 of the ROTAX®Operator’s Manual for 912 S Engines.
(c) Propeller MTV-21 related Manuals and Publications
mt-Propeller Entwicklung GmbH
Flugplatz Straubing- Wallmühle
D-94348 Atting
Tel: ++49 (0)9429-9409-0
Fax: ++49 (0)9429-8432
Internet: www.mt-propeller.com
E-Mail: [e-mail]

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AQUILA AT01-100A (N/VFR) Section 2
LIMITATIONS
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SECTION 2
LIMITATIONS
Page
2.1 INTRODUCTION 2-2
2.2 AIRSPEED LIMITATIONS 2-2
2.3 AIRSPEED 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 POWER PLANT INSTRUMENT MARKINGS 2-5
2.6 OTHER INSTRUMENT MARKINGS 2-5
2.7 WEIGHT LIMITS 2-6
2.8 CENTER OF GRAVITY LIMITS 2-6
2.9 MANEUVER LIMITS 2-6
2.10 FLIGHT LOAD FACTORS 2-7
2.11 CREW 2-7
2.12 KINDS OF OPERATION LIMITS / MINIMUM EQUIPMENT 2-8
2.13 FUEL LIMITATIONS 2-9
2.14 TEMPERATURE LIMITATIONS 2-9
2.15 OPERATING ALTITUDE 2-9
2.16 PLACARDS 2-10

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2.1 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.
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 overloading the aircraft
structure.
VFE
Maximum flap extended speed 90 Do not exceed this speed with flaps in T/O or
LDG position.
VNO
Maximum structural cruising
speed 130 Do not exceed this speed except in smooth
air, and then only with caution.
VNE
Never exceed speed 165 Do not exceed this speed in any operational
condition.

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2.3 AIRSPEED INDICATOR MARKINGS
The airspeeds given below are expressed in Indicated Airspeeds (IAS):
Marking (IAS) [kts] Remarks
White arc 39-90 Full flap operating range
Green arc 49-130 Normal operating range
Yellow arc 130-165 Operations in this region must be conducted with
caution and only in smooth air.
Red line 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 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 as propeller speeds, unlike the data in the Engine Operator's Manual.
c) Power Plant Limitations
Maximum Takeoff Power: 98.6 BHP (73.5 kW)
Maximum Takeoff Prop Speed (5 min.): 2385 RPM
Maximum Continuous Power: 92.5 BHP (69.0 kW)
Maximum Continuous Prop Speed: 2260 RPM

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d) 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)
e) Fuel Pressure
Minimum: red warning light
f) Oil Temperature
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 engine must be preheated.
2.4.2 Propeller
a) Manufacturer: mt-Propeller Entwicklung GmbH, Atting, Germany
b) Model: MTV-21-A/170-05
c) Propeller diameter: (66.9 in) 1,70 m
d) Propeller speed limitations
Maximum take-off propeller speed (max. 5 min): 2385 RPM
Maximum continuous propeller speed: 2260 RPM
** old type of cylinder head at cylinder no. 3 (see SB-AT01-029)

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2.5 MARKINGS ON POWER PLANT INSTRUMENTS
The following table shows the instrument markings on the power plants and their meaning.
Instrument Red Line
(minimum)
Green 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**)
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)
** old type of cylinder head at cylinder no. 3 (see SB-AT01-029)
2.6 MARKINGS ON OTHER INSTRUMENTS
Instrument Red Arc
(minimum)
Green / Red or
Yellow Arc
(caution)
Green Arc
(normal operating
range)
Red Arc
(maximum)
Voltmeter
[V] 8 – 11 11 – 12 12 – 15 15 – 16
Amperemeter
[A] --- --- --- ---

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2.7 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. The stall speed will
increase, so that the instrument markings are no longer accurate.
2.8 CENTER OF GRAVITY LIMITS
The reference datum is located at the wing 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 aircraft.
The procedure to determine the center of gravity location for flight is provided in Section 6 of
this handbook.
2.9 MANEUVER LIMITS
The aircraft is certificated in accordance to the JAR-VLA. That certification includes the
following maneuvers:
a) All normal, non acrobatic maneuvers.
b) Stalls: Wings level stall
c) Steep Turns: Angle of Bank ≤60°
d) Chandelle: Entry Speed 120kts
e) Lazy Eight: Entry Speed 110kts
NOTE
All acrobatic maneuvers as well as maneuvers with a bank angle exceeding 60° are prohibited.

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2.10 FLIGHT LOAD FACTORS
The following flight load factors may not be exceeded 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.
2.11 CREW
Maximum number of people on board: 2
Minimum crew: 1 Pilot
With only one person on board, the aircraft
may only be operated from the left seat.

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2.12 KINDS OF OPERATION LIMITS / MINIMUM EQUIPMENT
Certified for: visual flights by Day and Night
Table 1 For VFR by Day and Night*
Flight and navigational
instruments
•Altimeter (0 – 20,000 ft)
•Airspeed Indicator (0 – 200 kts)
•Magnetic Compass
•
Working timepiece with a seconds
hand***
•VHF Transceiver*
•VSI (±2000 ft/min)
•Attitude Indicator
•Slip Indicator
•Directional Gyro
•Outside Air Temperature (OAT)
Indicator
•VHF Transceiver*
•VOR Receiver*
•Transponder (XPDR)
Power Plant Instruments •Fuel gauge
•Oil Temperature Indicator
•Warning Light FUEL
•Oil Pressure Indicator
•Cylinder Head Temperature Indicator
•Manifold Pressure Gauge
•Ammeter
•Tachometer
•Voltmeter
•Warning Light ALT 1
•Warning Light ALT 2
•Warning Light VOLT
Lighting •Position Lights
•Anti Collision Lights
•Landing Lights
•Instrument lighting
•Cabin Lighting
•Flashlight
Other Equipment •Seat belts for each occupied seat
•Emergency Hammer
•Battery ≥ 26 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 a VHF Transceiver is not required for flights that do not leave the vicinity of an uncontrolled airfield
(§3a Abs. 3 d. Luftverkehrs-Ordnung). Regulations of other nations must still be observed (§ 21a Abs. 1 der
Luftverkehrs-Ordnung).
NOTE
For specific operations, additional equipment may be necessary. It is the aircraft operator’s
responsibility to observe the applicable requirements.

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2.13 FUEL LIMITATIONS
Left Fuel Tank Right Fuel Tank
Fuel capacity (total): 15.85 US gal (60.0 l) 15.85 US gal (60.0 l)
Usable fuel (total): 14.48 US gal (54.8 l) 14.48 US gal (54.0 l)
Unusable fuel: 1.37 US gal (5.2 l) 1.37 US gal (5.2 l)
NOTE
The amount of unusable fuel was determined with flap on LDG and VFE = 90 kts. It is the worst
case fuel supply configuration within section 4 “NORMAL PROCEDURES”.
For approved fuel grades, please refer to paragraph 1.8.
2.14 TEMPERATURE LIMITATIONS
Parts of the aircraft structure that are exposed to direct vertical sunlight must be painted
WHITE.
2.15 OPERATING ALTITUDE
The Aquila AT01-100 has a maximum operating altitude of 14,500 ft.

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2.16 PLACARDS
•On the instrument panel, in the lower middle section of the panel:
•On the instrument panel below the Airspeed Indicator:
MANEUVERING SPEED
VA= 112 KIAS
•On the inner surface of the baggage compartment door:

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AQUILA AT01-100A (N/VFR) SECTION 3
EMERGENCY PROCEDURES
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SECTION 3
EMERGENCY PROCEDURES
Page
3.1 INTRODUCTION 3-3
3.1.1 Resetting circuit-breakers 3-3
3.2 AIRSPEEDS FOR EMERGENCY OPERATION 3-3
3.3 ENGINE FAILURES – CHECKLISTS 3-4
3.3.1
3.3.2
3.3.3
Engine Failure During the Take-off Run
Engine Failure Immediately After Take-off
In-flight Engine 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 3-9
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
3-9
3-9
3-9
3-9
3.6 INADVERTENT FLIGHT INTO ICING CONDITIONS 3-10
3.7 SPIN RECOVERY PROCEDURE 3-11
3.8 POWER-OFF GLIDE 3-11
3.9 LANDING WITH A FLAT TIRE 3-12
3.10 ELECTRICAL SYSTEM MALFUNCTIONS 3-12
3.10.1
3.10.2
3.10.3
Complete Electrical System Failure
Alternator Failure (ALT 1, ALT 2)
Low Voltage Indication
3-12
3-13
3-16
3.11 FLAP CONTROL SYSTEM MALFUNCTIONS 3-17

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3.12 TRIM CONTROL SYSTEM FAILURES 3-17
3.12.1
3.12.2 Trim System Inoperative Trim Actuator Runaway 3-17 3-18
3.13 AVIONICS MALFUNCTIONS 3-18
3.13.1
3.13.2
3.13.3
Complete Avionics Failure
Receive Mode Failure of COM-Equipment
Transmit Mode Failure of COM-Equipment
3-18
3-18
3-18
3.14 STARTER MALFUNCTION 3-19
3.15 IN-FLIGHT FAILURES AND MALFUNCTIONS 3-19
3.15.1 Inadvertent Release and Opening of the Canopy in flight 3-19

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EMERGENCY PROCEDURES
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3.1 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.
However, should an emergency situation occur, the procedures provided here are
recommended to correct the problem and master the situation.
Not all types of emergency situations or combinations can be described in the POH. A pilot
must therefore 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 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 reset if it is needed for continued safe
flight and landing. In extreme cases, resetting a circuit breaker may cause an electrical fire.
A circuit breaker or safety switch should only be reset once and be inspected after flight.
3.2 AIRSPEEDS FOR EMERGENCY OPERATION
Airspeed (IAS) [kts]
Maneuvering speed VA 112
Speed for best glide ratio
Flaps UP
Flaps T/O
78
73
Precautionary landing with / without engine power
Flaps LDG 60
Landing without engine power
Flaps T/O
Flaps UP
65
70

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3.3 ENGINE FAILURES – CHECKLISTS
3.3.1 Engine Failure before Take-off
1. Throttle IDLE
2. Brakes APPLY as required
3.3.2 Engine Failure Immediately After Take-off and during Climb
1. 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.
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 switch ON
4. Ignition switch BOTH
5. Throttle wide OPEN
6. Propeller control lever START position
7. Choke PRESS (OFF)
8. Carburetor heat PULL (ON)
Before landing (if possible):
9. Fuel selector valve OFF
10. Ignition switch OFF
11. ALT1 / BAT switch OFF
WARNING
With BAT switch in OFF position: Stall warning system inoperative and flap
position cannot be changed !