Aquila A211 User manual

MAINTENANCE MANUAL
AQUILA AT01-100
A
MAINTENANCE MANUAL
AQUILA AT01-100 (A211)
AQUILA AT01-200 (A212)
Doc.-No. MM-AT01-1020-110
This document is protected by copyright. All associated rights, in particular those of translation, reprinting, reproduction
by photo mechanical or similar means and storing in data processing facilities in whole or part are reserved.
The technical content of this document is approved under the authority of DOA ref. EASA.21J.025.
AQUILA Aviation International GmbH Phone:++49 33 731 707 - 0
Flugplatz Fax: ++49 33 731 707 - 11
14959 Schönhagen e-mail: [email protected]
AQUILA Aviation International GmbH

MAINTENANCE MANUAL
AQUILA AT01-100
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MAINTENANCE MANUAL
AQUILA AT01-100/200
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Revision
Number
Revision
Number
Date of
Revision
Date of
Revision
Date
Inserted
Date
Inserted
By By
RECORD OF REVISIONS
Record of Revisions
A.01 30.04.13
A.02 26.08.13
A.03 24.10.13
A.04 02.03.15
A.05 20.08.15
A.06 29.02.16
A.07 10.06.16
A.08 09.10.18

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Temp. Revision
Number
Page Date of
Revision By By
Date
Removed
RECORD OF TEMPORARY REVISIONS
Record of Temp. Revisions
01 05-10-00 p.1 & 3 11.06.14 20.08.15
02 05-20-00 p.7 14.08.14 20.08.15
76-00-00 p.203
& 204

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MAINTENANCE MANUAL
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Revision
Number
Revision
Number
Date of
Revision
Date of
Revision
HIGHLIGHTS OF REVISIONS
Highlights of Revisions
Reason for Revision Reason for Revision
A.01 30.04.13 Initial issue.
A.02 26.08.13 SB-AT01-027
A.03 24.10.13 FAA validation
(airworthiness limitations,
wire routing diagrams);
lubrication revised;
standard torque ROTAX
engine mount revised
A.04 02.03.15 Life time limit,
6000 hour inspection
A.05 20.08.15 Fuel quantity indicating
system calibration
procedures added;
TBO’s and maintenance
checklist revised;
Temporary revisons 1
& 2 incorporated
A.06 29.02.16 Control surface ply
lay-up added; repair
procedures revised
A.07 10.06.16 6000h check & TBOs
added; battery check;
wing bolts safetying
A.08 09.10.18 Beringer: new axle
and new wheels;
Rotax: new spark plugs

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MAINTENANCE MANUAL
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LIST OF EFFECTIVE CHAPTERS
LIST OF EFFECTIVE CHAPTERS
Chapter Title Date*
GENERAL
Table of Contents 10.06.16
Introduction 30.04.13
04 Airworthiness Limitations 02.03.15
05 Time Limits / Maintenance Checks 10.06.16
06 Dimensions and Areas 30.04.13
07 Lifting & Shoring 30.04.13
08 Leveling and Weighing 30.04.13
09 Towing and Taxiing 30.04.13
10 Parking, Mooring, Storage & Return to Service 30.04.13
11 Placards and Markings 30.04.13
12 Servicing 24.10.13
AIRFRAME SYSTEMS
20 Standard Practices Airframe 09.10.18
21 Ventilation and Heating 30.04.13
23 Communications 30.04.13
24 Electrical Power 10.06.16
25 Equipment and Furnishings 30.04.13
27 Flight Controls 30.04.13
28 Fuel 20.08.15
31 Indicating/Recording Systems 30.04.13
32 Landing Gear 09.10.18
33 Lights 30.04.13
34 Navigation 30.04.13
STRUCTURES
51 Structures 29.02.16
52 Doors 30.04.13
53 Fuselage 30.04.13
55 Stabilizers 30.04.13
56 Windows 30.04.13
57 Wings 10.06.16
PROPELLER
61 Propeller 30.04.13
List of Chapters
09.10.18
Page 1

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LIST OF EFFECTIVE CHAPTERS
POWER PLANT
71 Power Plant 30.04.13
74 Ignition 09.10.18
75 Cooling System 30.04.13
76 Engine Controls 20.08.15
77 Engine Indicating 30.04.13
78 Exhaust 30.04.13
79 Oil 30.04.13
80 Starting 30.04.13
91 Charts and Wiring Diagrams 24.10.13
* The date refers to the issue / revision date of the respective chapter.
LIST OF EFFECTIVE CHAPTERS
Chapter Title Date*
List of Chapters
09.10.18
Page 2
The technical content of this document (revision A.08) is approved under the authority of
DOA ref. EASA.21J.025.
Date, Signature Office of Airworthiness

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CHAPTER 20
STANDARD PRACTICES - AIRFRAME

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Page 1
20 - TOC
TABLE OF CONTENTS
Chapter
Section
Title Subject Page
STANDARD PRACTICES AIRFRAME - GENERAL.....................................20-00-00 1
Introduction 20-00-00 1
General Description 20-00-00 1
FASTENER IDENTIFICATION AND TORQUE DATA...............................20-10-00 1
General 20-10-00 1
Bolt Types 20-10-00 1
Torques 20-10-00 2
CONVERSION DATA.......................................................................................20-11-00 1
General 20-11-00 1
Conversion Factors 20-11-00 1
Equivalents for Standard Values 20-11-00 3
Standard Practices
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20-00-00
STANDARD PRACTICES AIRFRAME - GENERAL
1. Introduction
A. This chapter describes standard maintenance practices applicable to the entire airframe and
related systems. Maintenance procedures which are unique to a specific system / component / part
are described in the corresponding chapter.
B. As far as the maintenance of the AQUILA AT01 is concerned, there are no standard practices or
relevant safety regulations, which require special knowledge other than that which is commonly
expected for the maintenance of small aircraft. Therefore, this chapter should serve basically as a
source for conversion data.
2. General Description
Below a brief description and intended purpose of each section of this chapter is given.
A. Section 20-00-00 - Standard Practices Airframe - General. This section provides a general overview
of content and purpose of the chapter.
B. Section 20-10-00 - Conversion Data. This section provides various formulae for converting metric,
Imperial and US measurements.
Standard Practices
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Page 1

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FASTENER IDENTIFICATION AND TORQUE DATA
1. General
A. This section contains information concerning the identification of bolts, the correct usage of bolts
and nuts and torque data.
CAUTION: OBSERVE STANDARD OR TORQUE VALUES RECOMMENDED BY THE
MANUFACTURER AND MAKE SURE THE RECOMMENDED SAFETYING
DEVICE FOR EVERY FASTENER IS APPLIED.
2. Bolt Types
A. The bolts used fulfill AN, MS, LN and DIN specifications. They can be identified by code
marking(s) on the bolt heads. These markings generally denote the material of which the bolt is
made, whether the bolt is a standard type or a special purpose bolt and sometimes include the
manufacturer.
10.6
VEB manufacturer
property class
Bolt heads marked with “x” indicate
a non-corrosion resistant steel bolt.
Bolt heads marked with a dash indicate
a corrosion resistant steel bolt.
AN-BOLT
DIN-BOLT
surface
cadmium plated
zink coated
C
SPEC
5
C
AN standard
steel bolt
AN standard
steel bolt
AN standard
steel bolt
aluminun
alloy (2024)
bolt
special bolt
special bolt special bolt
NAC close
tolerance bolt
63-59131
AE
R
O
Typical Aircraft Bolt Markings
Figure 1
20-10-00 Page 1
Standard Practices
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3. Torques
NOTE: When a specific torque is not provided in the maintenance instructions contained in this
maintenance manual, use the standard torque patterns shown in table 201 respectively
the special torques in table 202.
A. A correct torque application is very important. Undertorque can result in unnecessary wear of
nuts and bolts, as well as the parts they secure. Overtorque can cause failure of a bolt or nut due
to the overstressing of the threaded areas. Uneven or additional loads that are applied to the
assembly may result in wear or premature failure. To ensure that correct torque is applied,
observe the following:
(1) Be sure that the torque applied is for the size of the bolt shank and not the wrench size.
(2) Calibrate the torque wrench at least once a year, or immediately after it has been misused or
dropped, to ensure continued accuracy.
(3) Be sure that bolt and nut threads are clean and dry, unless otherwise specified by the
manufacturer.
(4) Run the nut down to near contact with the washer or bearing surface and check the friction
drag torque required to turn the nut. Whenever possible, apply the torque to the nut and not
the bolt. This will reduce rotation of the bolt in the hole and reduce wear.
(5) Add the friction drag torque to the desired torque. This is referred to as "final torque," which
should register on the indicator or setting for a snap-over type torque wrench.
(6) Apply a smooth even pull when applying torque pressure. If rattling or a jerking motion
occurs during final torque, turn back the nut and retorque.
(7) Many uses of bolts in aircraft/engines require stretch checks prior to reuse. This requirement
is due primarily to bolt stretching caused by overtorquing.
(8) When installing a castle nut, start alignment with the cotter pin hole at the minimum
recommended torque plus friction drag torque.
(9) Do not exceed the maximum torque plus the friction drag. If the hole and nut castellation do
not align, change washer or nut and try again. Exceeding the maximum recommended
torque is not recommended.
(10) When torque is applied to bolt heads or cap screws, apply the recommended torque plus
friction drag torque.
(11) If special adapters are used which will change the effective length of the torque wrench, the
final torque indication or wrench setting must be adjusted accordingly. Determine the
torque wrench indication or setting with adapter installed as shown in figure 2.
B. Table 201/202 shows the recommended torque to be used when the manufacturer does not supply
a specific torque for maintenance procedures.
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Standard Practices
DIN and LN specifications
Thread size Torque values Torque values
Nm in.lbs
M4
M5
M6
M8
M10
M12
1.8
3.6
6.4
16
32
60
15.9
31.9
56.6
141.6
283.2
531.1
Table 201: Standard Torques
1)
Table 202: Special Torques
Part Torque (Nm / in.lbs) Remarks
Bolts attaching lap belts to fuselage structure
Bolts attaching inertia reel retractor of shoulder harness
to fuselage structure
Bolts attaching engine to ROTAX engine mount
Oil drain screw
Old spark plugs (P/N 297940)
New spark plugs (P/N 297656)
Main gear spring leaf attachment bolts to inner bracket
Fuel drainer
4 / 35
8 / 71
40 / 354
25 / 221
20 / 177
16 / 142
1) Refer to the appropriate ROTAX publications for engine parts.
45 / 398
- - tighten until the outer o-ring is snug
against the mating surface
NOTE: Castellated nuts (DIN 935, 937)
should be finger tightened.
Banjo bolts of the Beringer brake system 17 / 150
refer to Rotax SI-912-027 /
SI-914-028

MAINTENANCE MANUAL
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adapter drive centerline
adapter drive centerline
wrench drive centerline
wrench drive centerline
handgrip centerline
handgrip centerline
E
E
L
L
Y = apparent (indicated) torque
T = actual (desired) torque
L = effective length lever
E = effective length of extension
T = 14 Nm
L = 30 cm
Y = ?
E = 8 cm
T = 14 Nm
L = 30 cm
Y = ?
E = 8 cm
formula:
formula:
T x L
L + E =Y
T x L
L - E =Y
example:
example:
Torque Wrench with Adapters
Figure 2
1. Variant - The adapter increases the effective length of the torque wrench.
2. Variant - The adapter decreases the effective length of the torque wrench.
Y=
Y=
14 Nm x 0,3 m
14 Nm x 0,3 m
0,3 m + 0,08 m
0,3 m - 0,08 m
4,2 Nm
4,2 Nm
0,38
0,22
=11,05 Nm
=19,09 Nm
=
=
20-10-00 Page 4
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