Aquila AT01 Technical specifications

Aviation by Excellence AG
AIRPLANE FLIGHT MANUAL
AQUILA AT01
LBA Approved in Normal Category based on JAR-VLA.
This Airplane Flight Manual must be carried on board of the aircraft at all times and be kept
within the reach of the pilot during all flight operations. The amendment history and revision
status of each section of the Airplane Flight Manual are provided in the list of effective pages
and in the list of revisions.
This aircraft must be operated in compliance with the procedures and operating limits specified
herein.
SERIAL NO.: AQUILA AT01-
REGIST. NO.:
Revision A.01 was approved by the Luftfahrt-Bundesamt (LBA) on 30/08/2002 within the scope
of the type-certification. All revisions of section 2, 3, 4 and 5 beyond the scope of documentary
changes are subject to EASA-approval.
Doc. No. FM-AT01-1010-100E
First Issued: 05/06/2002
Cover Page Issue No.: A.18

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INTRODUCTION
With the AQUILA AT01 you acquired a very efficient training and utility aircraft, which can
be operated very easily and exhibit excellent handling qualities.
Reliable operation, handling and maintenance guarantee always trouble-free flights and
continued airworthiness.
For that, we recommend to read this Airplane Flight Manual thoroughly and adhere to the
operating instructions and recommendations given herein.
Furthermore, we recommend attending a type training course held by AQUILA company
trained personnel to obtain a "feeling" for the optimal operation of the aircraft within a
shorter period of time.
NOTE
All limitations, procedures and performance data contained in this handbook are EASA-/
LBA-approved and mandatory. Not paying attention to the procedures and limits of the
handbook can lead to a loss of liability by the manufacturer.
THE HANDBOOK
The Airplane Flight Manual has been prepared using the recommendations of JAR-VLA
Appendix H (issue 26/4/90) “Specimen Flight Manual for a Very Light Aeroplane”.
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 airplane. Tab dividers throughout the
handbook allow quick reference to each section. Tables of Contents are located at the
beginning of each section to aid locating 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 the AQUILA Aviation by
Excellence AG.
Copyright © by Aviation by Excellence AG
Schönhagen, Germany

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TABLE OF CONTENTS
SECTION
GENERAL 1
OPERATING LIMITATIONS (an approved section) 2
EMERGENCY PROCEDURES (an approved section) 3
NORMAL PROCEDURES (an approved section) 4
PERFORMANCE (an partly approved section) 5
WEIGHT AND BALANCE 6
DESCRIPTION OF THE AIRCRAFT AND ITS SYSTEMS 7
HANDLING, SERVICE AND MAINTENANCE 8
SUPPLEMENTS 9

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LIST OF EFFECTIVE PAGES
Section approved Issue
No.
Page Date
0 A.18 0-1 to 0-8 29/11/2010
1 A.12 1-1 to 1-12 17/09/2008
2 X A.12 2-1 to 2-20 17/09/2008
3 X A.12 3-1 to 3-16 17/09/2008
4 X A.18 4-1 to 4-20 29.11.2010
5 (X)* A.12 5-1 to 5-23 17/09/2008
6 A.12 6-1 to 6-14 17/09/2008
7 A.14 7-1 to 7-32 03/09/2009
8 A.12 8-1 to 8-8 17/09/2008
9 A.17 9-1 to 9-3 07/10/2010
- partly approved

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LIST OF REVISIONS
All implementations of revisions to this manual, except individual weight and balance
data, should be entered in the record of revisions on the next page. Revisions must either
be approved by the EASA or, in the case of documentary changes in accordance with
Part 21A.263©(4), by the Design Organisation of AQUILA Aviation by Excellence AG.
Additions and revisions to the 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 pages of the revised section.
The operation of the AQUILA AT01 is only permitted with an Airplane Flight Manual in the
current effective status carried on board.
Please refer to our web page www.aquila-aviation.de whenever the revision status of
your Airplane Flight Manual is in question.
Issue
No.
Description of Revisions Revised
Section(s)
Approval by
AQUILA*/EASA
Date/Signature
A.01 First Issue Alle 30/08/2002
A.02 Installation of Garmin Avionic 0,2,9 13/05/2003
A.03 Editorial corrections 0,4,5,7 16/05/2003
A.04 Supplements for Bendix King equipment 0,9 09/07/2003
A.05 External Power, Supplement for Pointer
ELT 0,7,9 09/10/2003
A.06 Winterization Kit 0,2,9 10/03/2004
A.07 KANNAD 406 AF, ELT 0,9 23/06/2005
A.08 Supplements for Garmin Avionic 0,1,4,9 30/06/2005
A.09 Supplement for Bendix King KT 73 0,9 08/07/2005
A.10 Supplement for ARTEX ME406, ELT 0,9 07/03/2008
A.11 Introduction of new Emergency Proc. And
various AFM-Supplements 0,3,9 28/08/2008 (EASA)

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Issue
No.
Description of Revisions Revised
Section(s)
Approval by
AQUILA*/EASA
Date/Signature
A.12 Documentary changes All 28.11.2008
A.13 Supplement Garrecht Mode-S
Transponder 0,9 19/03/2009
A.14 Supplement for Day/Night-VFR-
Operation 0,7,9 03/09/09 (25.03.2010 EASA)
A.15 Supplement ASPEN EFD 1000 PFD/MFD 0,9 07/12/2009
A.16 Supplement GARMIN G500-System 0,9 22.07.2010
A.17 Changes in supplement for GARMIN
G500-sytem 0,9 07.10.2010 (15.11.2010 EASA)
A.18 Normal procedure – Actions introduced by
SB-AT01-020 0,4 29.11.2010 (14.01.2011 EASA)
APPROVAL*
Issue A.18 of the Airplane Flight Manual is approved within the approval of Major-Change
AT01-00438 Rev.A02 by EASA.
14. Jan. 2011 10033370
Date EASA-approval

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RECORD OF REVISIONS
When a new revision to the Airplane Flight Manual is issued, the corresponding sections
have to be removed and replaced by the pages of the revised sections.
Only entire sections will be changed and have to be replaced. Each time, when the
incorporation of a revision is accomplished, an endorsement has to be made in the record
of revisions shown below.
Issue No. Revised
Sections Date of Issue Date of insertion: Inserted by:
A.01 All 05/06/2002 --- ---
A.02 0,2,9 20/11/2002
A.03 0,4,5,7 15/04/2003
A.04 0,9 19/05/2003
A.05 0,7,9 30/09/2003
A.06 0,2,9 10/02/2004
A.07 0,9 30/07/2004
A.08 0,1,4,9 30/06/2005
A.09 0,9 05/07/2005
A.10 0,9 05/03/2006
A.11 0,3,9 30/11/2007
A.12 All 17/09/2008
A.13 0,9 19/03/2009
A.14 0,7,9 03/09/2009
A.15 0,9 07/12/2009
A.16 0,9 22/7/2010
A.17 0,9 07/10/2010
A.18 0,4 29/11/2010

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Purchase of Technical Publications
To guarantee safe operation and correct maintenance of the aircraft AQUILA AT01, all
manuals and technical publications must be kept in the current effective status.
All manuals and technical publications relating to the aircraft AQUILA AT01 are available
from the companies listed below:
(a) AQUILA AT01 related Manuals and Publications
AQUILA Aviation by Excellence AG
Flugplatz
D-14959 SCHÖNHAGEN
Tel: [phone]
Fax: [phone]
E-Mail: [email protected]
Internet: http://www.aquila-aviation.de
(b) Engine ROTAX 912 S related Manuals and Publications
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: [phone]
Fax: [phone]
Internet: www.mt-propeller.com
E-mail: [email protected]

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SECTION 1
GENERAL
Page
1.1 INTRODUCTION 1-2
1.2 AIRCRAFT TYPE CERTIFICATION 1-2
1.3 WARNING, CAUTIONS AND NOTES 1-3
1.4 AIRCRAFT PRINCIPAL 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 – THREE VIEW DRAWING 1-5
1.6 ENGINE 1-6
1.7 PROPELLER 1-6
1.8 FUEL 1-6
1.9 ENGINE 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 ABBREVIATIONS 1-9
1.12 CONVERSION FACTORS 1-11

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1.1 INTRODUCTION
This Airplane Flight Manual contains all information that the pilot and instructor need for
safe aircraft operation and to get the optimum utility from the AQUILA AT01.
It includes all data required in accordance with JAR-VLA and additional information
provided by the manufacturer and type certificate holder for maximum utilization as an
operating guide for the pilot.
This Manual consists of eight sections which cover all operational aspects of a standard
equipped aircraft. Optional equipment which has been installed on request of the
customer (COM, NAV, GPS and others) is considered in Section 9 "Supplements" of
this Manual.
Information regarding approved equipment that may be installed into the AQUILA AT01
is provided in Section 6, paragraph 6.5 or in the approved equipment overview list in the
Maintenance Manual, respectively.
1.2 Aircraft Type Certification
The aircraft model AQUILA AT01 is type-certificated 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.
The Type Certificate under the Type Certificate Data Sheet No. 1106 has been issued
on 21/09/2001.
The aircraft is certificated in the category: NORMAL
Noise Certificate according to: Noise Requirements for Aircraft (LSL), Chapter X
Additional Noise Requirements: Airfield Noise Requirements, Issue 05/01/1999
Approved Kinds of Operation: DAY-VFR

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1.3 WARNING, CAUTIONS AND NOTES
Throughout the text, special text boxes termed as WARNING, CAUTION and NOTE are
used to emphasize and address general remarks and special characteristics pertaining
to aircraft handling as well as operation. These terms are defined as follows:
WARNING
Procedures, practices, etc. which may result in personal injury or loss of life if not
thoroughly adhered to. The issues addressed under these text boxes directly affect the
airworthiness and the safe operation of the airplane.
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 airplane.
NOTE
Calls attention to additional procedures or information which are not directly associated
with flight safety but nevertheless important or unusual to standard practices.

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1.4 AIRCRAFT PRINCIPAL DIMENSIONS
1.4.1 Overall Dimensions
Wing Span: 10.3 m
Length: 7.35 m
Height: 2.4 m
1.4.2 Wings
Airfoil: HQ-XX mod.
Area: 10.5 m²
Aspect Ratio: 10.1
Mean Aerodynamic
Chord (MAC): 1.07 m
1.4.3 Horizontal Stabilizer / Elevator
Area: 2.0 m²
Span: 3.0 m
1.4.4 Fuselage and Vertical Stabilizer / Rudder
Max. Width 1.20 m
Length 7.35 m
1.4.5 Landing Gear
Wheel Track: 1.938 m
Wheel Base: 1.685 m
Tire Sizes
Nose Gear: 5.00-5 (Cleveland Wheels & Brakes)
Main Gear: 5.00-5 (Cleveland Wheels & Brakes)
Tire Pressure
Nose Gear: 2.0 bar
Main Gear: 2.5 bar

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1.5 AQUILA AT01 – Three View Drawing

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1.6 ENGINE
The ROTAX
®
912 S3 is a 4-cylinder 4-stroke engine with ram air cooled and horizontally
opposed cylinders as well as 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.
Reduction Ratio of internal gearbox: 2.43 : 1
Displacement: 1352 cm³
Take-Off Performance: 69.0 kW
at a Propeller Shaft Speed of 2263 1/min
1.7 PROPELLER
Two-blade, constant speed propeller manufactured by mt-Propeller Entwicklung GmbH.
Type: MTV-21-A/175-05
Hydraulically Controlled Variable
Pitch (Constant Speed) Propeller
Max. Propeller Diameter: 175 cm
1.8 FUEL
The following fuel grades are approved for usage (min. RON 95):
EN228 Premium
EN228 Premium plus
AVGAS 100LL
Left Fuel Tank Right Fuel Tank
Fuel Capacity (total): 60 60 Litres
Usable Fuel (total) : 54.8 54.8 Litres
Unusable Fuel: 5.2 5.2 Litres
Due to the higher lead content in AVGAS, the wear of the valve seats, the deposits in
the combustion chamber and lead sediments in the lubrication system will increase
when using this type of fuel. Therefore, use AVGAS only if you encounter problems with
vapour lock or if the other fuel types are not available (refer also to the Operators
Manual for ROTAXEngine Type 912 Series, latest revision).

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1.9 ENGINE OIL AND COOLANT
1.9.1 Engine Oil
Use only oil with API classification “SG” or higher.
Heavy duty 4-stroke motor cycle oils meet normally all the requirements.
For more information regarding engine oil selection, refer to the Operator’s Manual for
all versions of 912 series engines, section 10.2.3, and to ROTAX
®
Service Instruction
SI-912-016, latest revision.
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 types!
When operating the engine with AVGAS, more frequent oil changes will be required!
(refer also to ROTAX
®
Service Instruction SI-912-016, latest rev., for more information)
Max. Oil Capacity : 3.0 Litres
Quantity between Max/Min 0.45 Litres
Max. Oil Consumption: 0.06 Litres/h

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1.9.2 Engine Coolant
Only the following water-free coolant concentrate based on propylene glycol is
approved for the usage in the AQUILA AT01.
Mixture Ratio %
Designation Concentrate Water
EVANS NPG+100 0
When correctly applied (100% coolant concentration), there is sufficient protection
against vapour bubble formation, freezing or thickening of the coolant within the
operating limits.
WARNING
The coolant concentrate EVANS NPG+must not be mixed with conventional
glycol/water coolant or with additives. The disregarding of this warning can lead to
damages to the cooling system and, as a result, to motor damages, since the properties
of the coolant do not longer exist (refer also to ROTAX
®
SB-912-043, latest revision, as
well as ROTAX Service Instruction SI-912-016, latest revision, for more information).
CAUTION
Qualitatively inferior and contaminated coolant may lead to deposits in the
cooling system which may result in an insufficient engine cooling.
Coolant Quantity Total: Minimum: 2.4 Litres
Maximum: 2.5 Litres
Coolant Quantity in the Minimum: 0.1 Litres
Overflow Bottle: Maximum: 0.2 Litres
1.10 WEIGHTS
Max. Takeoff Weight (MTOW): 750 kg
Max. Landing Weight (MLW): 750 kg
Empty Weight: Refer to section 6
Max. Weight in Baggage Compartment: 40 kg
(All baggage must be adequately strapped and secured)
Max. Wing Loading: 71.4 kg/m²
Min. Wing Loading: circa 52.6 kg/m²

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1.11 TERMINOLOGY AND ABBREVIATIONS
1.11.1 Airspeeds
IAS: (Indicated Airspeed), Speed as shown on the airspeed indicator.
KIAS: IAS expressed in Knots
CAS: (Calibrated Airspeed), Means the indicated airspeed, corrected for position
and instrument error. CAS is equal to true airspeed in standard
atmosphere conditions at sea level.
KCAS: CAS expressed in Knots
TAS: (True Airspeed), Airspeed relative to undisturbed air, which is the CAS
corrected for altitude, temperature and compressibility.
GS: (Ground speed), Airspeed relative to ground.
V
A
: Manoeuvring Speed
V
S
: Stalling speed without engine power.
V
S0
: Stalling speed without engine power in the landing configuration.
V
X
: Best Angle-of-Climb Speed
V
Y
: Best Rate-of-Climb Speed
V
FE
: Maximum Flap Extended Speed
V
NE
: Never Exceed Speed - The speed limit that must not be exceeded at any
time.
V
NO
: Maximum Structural Cruising Speed is the speed that should not be
exceeded except in smooth air and then only with caution.
1.11.2 Weight and Balance
Reference Datum An imaginary vertical plane from which all horizontal
distances are measured for balance purposes.
Reference line fixed horizontal reference line

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Lever Arm: The horizontal distance from the reference datum to the
centre of gravity (C.G.) of an item.
Moment: The product of the weight of an item multiplied by its lever
arm.
Empty Weight: Weight of the aircraft including unusable fuel, full operating
liquids and full oil.
Max. Takeoff Weight: Maximum permissible weight approved for the conduction of
the takeoff run.
Useful Load: Difference between takeoff weight and basic empty weight.
Usable Fuel : Fuel available for flight planning.
Unusable Fuel: Fuel remaining in the fuel tanks that cannot be safely used in
flight.
Centre of Gravity (C.G.):The point at which an aircraft would be in the balanced
condition if seated/suspended on that point (centre of mass).
MAC: Mean aerodynamic chord
1.11.3 Meteorological Terminology
OAT: Outside Air Temperature
VFR, day day: (SR) Sunrise-30 min to (SS) Sunset+30 min
1.11.4 Engine and Performance
Takeoff Power: Maximum power permissible for takeoff.
Max. Continuous Power: Maximum power permitted for continuous operation.
1.11.5 Miscellaneous
Serial No. (S/N): Serial Number of the Aircraft
Part No. (P/N): Part Number
GFRP: Glass Fibre Reinforced Plastic
CFRP: Carbon Fibre Reinforced Plastic
ACL: Anti Collision Light

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1.12 CONVERSION FACTORS
1.12.1 Length
1 ft = 0.304 m
1 in = 25.4 mm
1.12.2 Airspeed
1 kts = 1.852 km/h
1 mph = 1.609 km/h
1.12.3 Pressure
1 hPa = 100 N/m² = 1 mbar
1 in Hg = 33.865 hPa
1 psi = 68.97 mbar
1.12.4 Mass (“Weight”)
1 lbs = 0.454 kg
1.12.5 Volume
1 US Gallon = 3.78 Litre
1 Imperial Gallon = 4.546 Litre
1.12.6 Temperature
(t)°C (Celsius) = 5/9 ((t)°F - 32)
(t)°F (Fahrenheit) = 9/5 (t)°C + 32