MW Fly B22 AeroPower Original operating instructions

Manual for B22 Revision 1.0 – 02/05/2013
B22 AeroPower
QUICK INSTALLATION

Manual for B22 Revision 1.0 – 07/02/2013
Manual Q – Quick Installation -2
MANUAL Q
Before attempting any engine start carefully read Manual A containing
important safety information. Not following safety procedures could cause
severe injury or loss of life. Consult the aircraft instruction manual for more
information on safety.

Manual for B22 Revision 1.0 – 07/02/2013
Manual Q – Quick Installation -3
All information, illustrations, instructions and technical data contained in this manual has been upgraded before
printing. MW Fly reserves the right to modify, correct or upgrade general data at any time without any obligation or
prior consent from third parties. Publication of any part of this document without written consent of MW Fly is
strictly prohibited.
This Manual forms part of the engine and must be kept safe. It must accompany the engine in case of sale to a new
owner. The original document is written in Italian and this language will be used to settle any dispute of a legal or
technical nature.

Manual for B22 Revision 1.0 – 07/02/2013
Manual Q – Quick Installation -4
Q.1. SUMMARY
Q.2. INTRODUCTION 8
Q.2.1. Statement 8
Q.2.2. Consultation Notes 8
Q.2.3. Identification Data 9
A.2.4. MW Fly Authorized Service Centers 9
Q.3. SAFETY 10
Q.3.1. Statement 10
Q.3.2. General rules 10
Q.3.3. Modifications and accessory 10
Q.3.4. Location and identification of components 10
Q.4. TECHNICAL AND OPERATIONAL CARACTERISTICS 11
Q.4.1. Dimensions 11
Q.4.2. Weights 14
Q.4.2.1. Optional accessory 15
Q.4.3. Position of center of gravity CoG 15
Q.4.4. Propeller direction rotation 15
Q.4.5. Permissible load on propeller flange 16
Q.4.6. Operational limits 17
Q.5. PREPARING FOR INSTALLATION 18
Q.5.1. Engine handling 18
Q.6. ENGINE POSITION AND ATTACHMENT 19
Q.6.1. Assembly position 19
Q.6.1.1. Permitted deviation angles 19
Q.6.2. Description of the mounting points 20
Q.6.3. Maximum load permitted on the attachment point 24
Q.6.3.1. “R” attachment point 24
Q.6.3.2. “L” attachment point 24
Q.6.3.3. “F” attachment point 24
Q.6.4. Attachment on engine cradle 25
Q.7. EXHAUST SYSTEM 27
Q.7.1. Standard exhaust system 27
Q.7.1.1. Description 27
Q.7.1.2. Installation 27
Q.7.2. Operational limits 29
Q.7.3. Original accessories 30
Q.8. COOLING SYSTEM 31
Q.8.1. Description 31

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Manual Q – Quick Installation -5
Q.8.2. Operational limits and technical data 32
Q.8.2.1 fluids capacity 32
Q.8.3. Standard radiator and hoses 33
Q.8.3.1. Installation 33
Q.8.4. Recommended cooling fluid 34
Q.8.5. Cooling system refilling 35
Q.8.6. Fine setting 38
Q.8.6.1. Cooling system air intake dimension 38
Q.8.6.2. Measuring cooling fluid temperature 38
Q.8.6.3. Test and verifying system functionality 38
Q.9. LUBRICATION SYSTEM 40
Q.9.1. Description 40
Q.9.2. Operating limits and technical data 41
Q.9.2.1. Engine oil capacity 41
Q.9.3. Recommended lubricants 41
Q.9.4. Refilling method 42
Q.9.5. Final setting 44
Q.9.5.1. Engine oil pressure sensor check 44
Q.9.5.2. Engine oil temperature sensor check 44
Q.10. FUEL SYSTEM 45
Q.10.1. Description 45
Q.10.2. Operational limit and technical data 46
Q.10.2.1. Gascolator 46
Q.10.2.2. Hose tube and fitting 46
Q.10.2.3. Fuel selector valve 47
Q.10.3. Standard Fuel Delivery Module (FD-M) 47
Q.10.3.1. Description 47
Q.10.3.2. Installation 48
Q.10.4. Installation and dimensions 50
Q.10.5. Recommended fuel 52
Q.10.6. Fuel circuit purge 52
Q.10.7. Final setting 53
Q.10.7.1. Fuel hoses 53
Q.10.7.2. Fuel pressure check 53
Q.10.7.3. Fuel temperature Check 53
Q.11. AIR INTAKE SYSTEM AND ENGINE VENTILATION 55
Q.11.1. Description 55
Q.11.1.1. Air inlet system 55
Q.11.1.2. Engine ventilation 55
Q.11.1.3. Crank case ventilation 55
Q.11.2. General characteristics 55

Manual for B22 Revision 1.0 – 07/02/2013
Manual Q – Quick Installation -6
Q.11.2.1. Air filter 55
Q.11.2.2. Air intake manifold 55
Q.11.2.3. Throttle control cable 56
Q.11.2.4. Components operative limits 56
Q.11.3. General installation directive 56
Q.11.3.1. Air intake manifold removal 56
Q.11.3.2. Engine air intake 58
Q.11.3.3.Cowling air intake 58
Q.11.3.4.Throttle control system 59
Q.11.4.Final setting 60
Q.11.4.1. Intake air intake temperature check 60
Q.11.4.2. Manifold pressure check (MAP) 61
Q.11.4.3. Components temperature check 61
Q.12. INJECTION AND IGNITION SYSTEM 63
Q.12.1. Description 63
Q.12.1.1. Single ECU System 63
Q.13.1.2. Dual ECU System 63
Q.12.2. General characteristics 64
Q.12.3. Final tuning 64
Q.12.3.1. Operational ECU temperature check 64
Q.13.ELECTRICAL LOOM 66
Q.13.1. General characteristics 66
Q.13.1.1. Battery 66
Q.13.1.2. Master switch 66
Q.13.1.3. Toggle switch 66
Q.13.1.4. Start pushbutton switch 66
Q.13.1.5. Cockpit fuses 67
Q.13.2. Electric Hub Module (EH-M) relay and fuses 67
Q.13.2.1. Description 67
Q.13.2.2. Installation 68
Q.13.3. Electric diagram 69
Q.13.4. Implementation 71
Q.13.5. Connection of the electrical components 75
Q.13.5.1. Battery 75
Q.13.5.2. Generator and voltage regulator 76
Q.13.5.3. Starter motor relay 76
Q.14. REDUCTION GEAR BOX 77
Q.14.1. General characteristics 77
Q.14.1.1. Propeller flange 77
Q.14.1.2. Governor 78
Q.14.1.3. Oil capacity 79

Manual for B22 Revision 1.0 – 07/02/2013
Manual Q – Quick Installation -7
Q.14.2. Recommended lubricant 79
Q.14.3. Refilling reduction box 79
Q.14.4. Propeller 79
Q.14.4.1. Polar moment of inertia 79
Q.14.4.2.Propeller balance 80
Q.14.5. Final setting 80
Q.14.5.1. Gear oil temperature check 81
Q.15. INSTRUMENTATION SENSOR 81
Q.15.1. Flight instrumentation (HSA-M) 82
Q.16. POST INSTALLATION CHECK AND FINAL TEST 82
Q.16.1. Important safety advice 82
Q.16.2. First start-up 83
Q.16.3. Installation final test 84
Q.16.3.1. Ground test 84
Q.16.3.2. Max power test 84
Q.16.3.3. In flight test 85
Q.17. MANUAL UPDATE LIST 86

Manual for B22 Revision 1.0 – 07/02/2013
Manual Q – Quick Installation -8
Q.2. INTRODUCTION
Q.2.1. Statement
This manual describes how to install the standard B 22 AeroPower. Prior to commencing
work on engine installation it is crucial to read and understand the contents of this document.
This manual contains all basic information for correct installation and safe operation.
For additional or more detailed information consult the Operational Manual, the Maintenance
Manual and the Additional Maintenance Manual.
B22 AeroPower engine has not received any certification for aeronautical use.
It must be used exclusively on experimental aircraft where an engine failure
will not compromise flight safety. Its use in cetified aircraft is strictly
prohibited.
Engine installation must be done taking into consideration the governing aviation
law, rules and regulations in force in the country where the engine will be used.
Unless specifically stated, the engine is delivered DRY, without engine oil, gearbox
oil and cooling fluid. Before attempting the first start all levels must be topped up.
(A.10.4., A.15.4., A.9.6.).
The engine can only be started once installation is completed and propeller securely
mounted. Ignoring this recommendation could cause severe damage to cranking
system.
Q.2.2. Consultation Notes
This manual was originally printed in Italian. This will be the only language used for any
reference or dispute.
Symbols used in this manual have the following meaning.
WARNING: Not following this instruction can cause severe personal injury or
loss of life.
CAUTION: Not following this instruction could cause severe damage to the engine
or other components.
NOTE: Refers to supplementary information to better understand or execute an
instruction.
This symbol is used to indicate a list of actions or subjects with relation to inclusion: all of
the actions or options listed with this symbol must be verified.
oThis symbol is used to indicate a list of actions or subjects with relation to exclusion: only
one of the actions or options listed with this symbol must be verified.
This symbol is used to indicate a list of characteristics or components referring to a specific
part of the engine.
Manual for B22 Revision 1.0 – 07/02/2013
Manual Q – Quick Installation -8
Q.2. INTRODUCTION
Q.2.1. Statement
This manual describes how to install the standard B 22 AeroPower. Prior to commencing
work on engine installation it is crucial to read and understand the contents of this document.
This manual contains all basic information for correct installation and safe operation.
For additional or more detailed information consult the Operational Manual, the Maintenance
Manual and the Additional Maintenance Manual.
B22 AeroPower engine has not received any certification for aeronautical use.
It must be used exclusively on experimental aircraft where an engine failure
will not compromise flight safety. Its use in cetified aircraft is strictly
prohibited.
Engine installation must be done taking into consideration the governing aviation
law, rules and regulations in force in the country where the engine will be used.
Unless specifically stated, the engine is delivered DRY, without engine oil, gearbox
oil and cooling fluid. Before attempting the first start all levels must be topped up.
(A.10.4., A.15.4., A.9.6.).
The engine can only be started once installation is completed and propeller securely
mounted. Ignoring this recommendation could cause severe damage to cranking
system.
Q.2.2. Consultation Notes
This manual was originally printed in Italian. This will be the only language used for any
reference or dispute.
Symbols used in this manual have the following meaning.
WARNING: Not following this instruction can cause severe personal injury or
loss of life.
CAUTION: Not following this instruction could cause severe damage to the engine
or other components.
NOTE: Refers to supplementary information to better understand or execute an
instruction.
This symbol is used to indicate a list of actions or subjects with relation to inclusion: all of
the actions or options listed with this symbol must be verified.
oThis symbol is used to indicate a list of actions or subjects with relation to exclusion: only
one of the actions or options listed with this symbol must be verified.
This symbol is used to indicate a list of characteristics or components referring to a specific
part of the engine.
Manual for B22 Revision 1.0 – 07/02/2013
Manual Q – Quick Installation -8
Q.2. INTRODUCTION
Q.2.1. Statement
This manual describes how to install the standard B 22 AeroPower. Prior to commencing
work on engine installation it is crucial to read and understand the contents of this document.
This manual contains all basic information for correct installation and safe operation.
For additional or more detailed information consult the Operational Manual, the Maintenance
Manual and the Additional Maintenance Manual.
B22 AeroPower engine has not received any certification for aeronautical use.
It must be used exclusively on experimental aircraft where an engine failure
will not compromise flight safety. Its use in cetified aircraft is strictly
prohibited.
Engine installation must be done taking into consideration the governing aviation
law, rules and regulations in force in the country where the engine will be used.
Unless specifically stated, the engine is delivered DRY, without engine oil, gearbox
oil and cooling fluid. Before attempting the first start all levels must be topped up.
(A.10.4., A.15.4., A.9.6.).
The engine can only be started once installation is completed and propeller securely
mounted. Ignoring this recommendation could cause severe damage to cranking
system.
Q.2.2. Consultation Notes
This manual was originally printed in Italian. This will be the only language used for any
reference or dispute.
Symbols used in this manual have the following meaning.
WARNING: Not following this instruction can cause severe personal injury or
loss of life.
CAUTION: Not following this instruction could cause severe damage to the engine
or other components.
NOTE: Refers to supplementary information to better understand or execute an
instruction.
This symbol is used to indicate a list of actions or subjects with relation to inclusion: all of
the actions or options listed with this symbol must be verified.
oThis symbol is used to indicate a list of actions or subjects with relation to exclusion: only
one of the actions or options listed with this symbol must be verified.
This symbol is used to indicate a list of characteristics or components referring to a specific
part of the engine.

Manual for B22 Revision 1.0 – 07/02/2013
Manual Q – Quick Installation -9
Q.2.3. Identification Data
The Engine serial number is
located on the upper side of
crank case near oil dip stick.
It is composed of ten alpha
numeric codes where the third
and fourth symbol indicate
Model and Version, the
following four are the serial
number and the last two are
the year of manufacturing.
Identification code and
version is illustrated in chart
B.4.2.1.C.
API GL-5 OR HI GHER
C
H
E
C
B
I
F
O
R
E
F
L
G
H
T
K
E
SAE 85W/140
T
I
C
A
P
A
C
Y
3
.
0
G E A R
L
CTIVE AM PING ONTROL
O I L


API SG OR HIGHER
C
H
E
C
B
I
F
O
R
E
F
L
G
H
T
K
E
SAE 15W/50
T
I
C
A
P
A
C
8
.
2
Y
L


E N GI N E
O I L
Q.2.3.1.P
Deleting or modifying the serial number will revoke any warranty and obligation by MW Fly
toward current owner.
Provide the serial number on any request for an engine part or technical information.
A.2.4. MW Fly Authorized Service Centers
Contact the nearest service centre or web-site for any information regarding service, maintenance
or spare parts. (B.10. or www.mwfly.it).

Manual for B22 Revision 1.0 – 07/02/2013
Manual Q – Quick Installation -10
Q.3. SAFETY
Q.3.1. Statement
The onus to install MW Fly B22 engine is at the sole discretion and responsibility of the Original
Manufacturer, Home Builder or Aircraft Owner. MW Fly cannot assume responsibility for a
successful installation in a specific airframe due to the variety of designs existing in the market.
For this reasons MW Fly declines responsibility regarding damage to engine parts, accessories or
aircraft structure during the installation and use of this engine. The owner accepts the
responsibility and the risk in using this engine.
Q.3.2. General rules
Consult Advisory Safety, listed in chapter A.3.2. of Installation Manual.
Q.3.3. Modifications and accessory
Examine Safety Advisory listed in chapter A.3.3. of Installation Manual.
Q.3.4. Location and identification of components
Before commencing installation make sure you are familiar with the description
and location of all components. If in doubt consult section A.4.3.

Manual for B22 Revision 1.0 – 07/02/2013
Manual Q – Quick Installation -11
Q.4. TECHNICAL AND OPERATIONAL CARACTERISTICS
Q.4.1. Dimensions
STD hubØ4" - 6 holes M8x1.25
Ø13 bushings - CenteringØ47mm
E
C
Y
E
A
R
S
A
T
484
208
54
0
3C Y L 4C Y L
E
B
T
H
O
G
O
F
I
H
E
N
E
R L
F
P
E
N
W
H
O
T
S
G
S
Y
N
R
C
D
N N
E
V
E
A
0
.
Y
7
A
P
A
C
I
O
C
I
L
O
L
E
T
E
H
C
E
C
K
L
V
T
L
E
M
L
L
I
RESERVOIR
U
S
E
F
N
G
V
E
R
Y
2
C
E
H
A
E
PRESSURIZED
379
API SG OR HIGHER
B
SAE 15W/50
A
P
E N GI N E
H
T
121
155
0Prop axis



I
F
O
R
E
F
L
G
E
3
L
G
L
T
H
O
L
A
N
T
O
T /
2
N
E
P
U
K
N
O
Y
L
E
L
O
O
N
Y
C
Y
T
I
C
8
.
2
Y
L
O I L
MAX OPERATIN G TEMPERATURE 85°C
CHECK WIRI NG LOOM BEFORE FLIGHT -
OPERATING ELEC TRIC VOLTAGE 9-18V
IGITAL ONTROL
PROTECT BEFORE WASHING
NGINE
FLY
ULL UTHORITY
BY
H
E
144
C
K
C
A
C
0
155
164
129
00
mass
405
297
1C Y L2C Y L
Center of
508 568
Center of
mass
12
Prop axis
0
379
Throttle control 74
3m length
Lower position
Ø1.2 bowden
Max heat transfer
36kW at take off
27
Ø32 pipe
To radiator
27
From radiator
Ø32 pipe
Dim ensional w it hout gear box
190
221
112
0
INTAKE
EFFECT
RAM
FL Y
D
219
E
C
L
N
A
A
N
P
E
K
E
Y
D
R
Ø1.2 bowden 235
Upper position
3m length
288
Throttle control

Manual for B22 Revision 1.0 – 07/02/2013
Manual Q – Quick Installation -12
Q.4.1.1.P
Ø13 bushings - CenteringØ47mm
STD hubØ4" - 6 holes M8x1.25

209
0
144
98
84
121
0Prop axis
G E A RG EA R
T
ONTROL
C
CTIVE AMPING
E
K
R
O
F
B
H
G
L
F
I
O I LO I L
SAE 85W/140
E
C
E
H
A
P
A
C
I
T
L
0
.
3
Y
API GL-5 OR HIG HER
C

PRESSURIZED
R
U
I
L
A
560
284
3C YL C YL 4
O
H
W
N
E
H
N
L
I
E
C
A
E
N
N
V
E
P
H
C
A
L
O
C
O
C
L
E
R
V
K
E
C
E
A
D
E
P
O
B
F
RESERVOIR
E
H
C
E
V
E
L
G
7
S
T
I
L
T
I
Y
0
N
G
O
R
E
F
S
.
F
Y
M
T
H
T
379
L
8
L
I
API SG OR HIGHER
E N GI N EE N GI N E
G
T
H
Y
C
2
T
E
S
E
L
G
N
E
K
U
H
T
E
L
Y
A
E
N
Y
N
G
L
Y
L
T
S
3
/
C
O
O
L
O
A
L
O
R A
E
Y
P
T
O
N
N
2
O I LO I L
E
K
F
B
C
E
H
F
E
R
SAE 15W/50
O
C
C
A
P
A
C
I
Y
2
.
T
NGINE
PROTECT BEFORE WASHINGPROTECT BEFORE WASHING
MAX OPERATING TEMPERA TURE 85°C
OPERATING ELECTRIC VOLT AGE 9-18V
ONTROLUTHORITY
CHECK WIR ING L OOM BEFORE FLIGHT -
FLYBY
IGITALULL
0
209
Dim ensional w it h gear box
Center of
mass
68
247
0 0
205
88
0
188
Prop axis
107
0
56
Ø32 pipe
From radiator
mass
Center of
C YL 1
371
2C YL
481
644
584
379
34.5kW at take off
Throttle control
Lower position
3m length
Ø1.2 bowden
Max heat transfer
157
110
Ø32 pipe
To radiator
N
A
A
L
E
295
EFFECT
INTAKE
RAM
E
K
C
E
P
FL Y
D
R
D
Y
N
Throttle control
3m length
Upper position
Ø1.2 bowden
Prop axis 0
151
204
Q.4.1.2.P

Manual for B22 Revision 1.0 – 07/02/2013
Manual Q – Quick Installation -13
Prop axis
107
Center of mass
247
0
68
88
295
188
0 0
204
157
Ø1.2 bowden
3 m lenght
Throttle contol
0
Prop. axis
133
RAM
INTAKE
EFFECT
E
C
L
P
E
K
E
Y
D
N
A
D
R
FL Y
A
N
627
316
526
765
365
540
0 0
379
362
362
379
282
282
328
229
229
328
166
Ø116
Optional
166
Dimensional version with gear box and radiator + std. exhaust system
Q.4.1.3.P

Manual for B22 Revision 1.0 – 07/02/2013
Manual Q – Quick Installation -14
Version without gear box
Max dimension [mm]
direction -
direction +
total
Max along X axis
10
568
578
Max along Y axis
379
379
758
Max along Z axis
164
288
452
Q.4.1.1.C
Version with gear box
Max dimension [mm]
direction -
direction +
total
Max along X axis
10
644
654
Max along Y axis
379
379
758
Max along Z axis
247
204
451
Q.4.1.2.C
Version without gear box and standard radiator
and exhaust system
Max dimension [mm]
direction -
direction +
total
Max along X axis
10
689
699
Max along Y axis
379
379
758
Max along Z axis
443
288
731
Q.4.1.3.C
Version with gear box and standard radiator
standard exhaust system
Max dimension [mm]
direction -
direction +
total
Max along X axis
10
765
775
Max along Y axis
379
379
758
Max along Z axis
526
204
731
Q.4.1.4.C
The tolerance on the above measurement is ±5 millimeters.
Q.4.2. Weights
Table Q.4.2.1.C shows the dry weight of the engine and the weight with lubricants. The weight
includes all the accessories needed to fly (internal generator, voltage regulator, starter relay,
thermostat, water expansion tank, throttle control, fuel injection wiring loom, two ECU’s, rubber
mounting, air filter). Only the radiator coolant and exhaust system are not included in the weight
shown in the table.
Weight [Kg]
Dry
With lubricants
B22D*
80
82.8
B22H*
79.2
82
B22L
84.1
87.1
B22R
84.1
87.1
Q.4.2.1.C

Manual for B22 Revision 1.0 – 07/02/2013
Manual Q – Quick Installation -15
* data can be modified
Q.4.2.1. Optional accessory
Adapter for bed mount (4 pieces)
0.37 Kg
Exhaust system
~ 5.1 Kg
Coolant radiator kit
~ 1.7 Kg
Auxiliar fuel pump
0.66 Kg
Governor**
---
Propeller with hub **
---
HSA-M (without wiring loom)**
---
EH-M (Electric Hub Module)
~ 0.98 Kg
FD- M (Fuel Delivery Module)
~ 2.75 Kg
** data not available
Q.4.3. Position of center of gravity CoG
Version without gear box
Position of center of gravity
CoG [mm]
Engine
Engine with standard exhaust
system and liquid radiator
X axis
297
301
Y axis
0
0
Z axis
12
8
Q.4.3.1.C
Version with gear box
Position of center of gravity
CoG [mm]
Engine
Engine with standard exhaust
system and liquid radiator
X axis
371
375
Y axis
0
0
Z axis
-68
-64
Q.4.3.2.C
CoG: The above values refer to dry condition and can also be considered valid for the engine
filled with lubricants.
Q.4.4. Propeller direction rotation
Propeller rotation is viewed by standing in front of propeller (see picture Q4.4.1P and Q4.4.2P).
It is counter clockwise for the version without the gear box and clockwise for the version with the
gear box.

Manual for B22 Revision 1.0 – 07/02/2013
Manual Q – Quick Installation -16
Ver s ion w it h ge a r box
Q.4.4.1.P
Version w it hout gear box
Q.4.4.2.P
Never manually rotate the propeller in the opposite direction. This operation can
damage the automatic timing chain tensioners and also disengage the system on the
engine starter.
Q.4.5. Permissible load on propeller flange
The following table shows the max/radial and max/axial load on the propeller/transmission shaft.

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Manual Q – Quick Installation -17
Max load on the shaft [N]
Version without gear box
Version with gear box
Max axial continuous load
2000
2000
Max axial load
9000
7000
Max radial continuous load
8000
5000
Max radial
32000
19000
Q.4.5.1.C
In a standard engine application or fixed-wing aircraft the load on the propeller shaft is normally
under the limit indicated in the table. In an application with an engine on a rotary wing aircraft it
is necessary to keep in consideration the axial and radial load generated by the transmission belt
of the pre-rotator system or generated by the transmission belt on a helicopter.
Q.4.6. Operational limits
After the installation phase it is mandatory to check the working parameters of the engine
indicated in table Q.4.6.1.C. This check has to be done first on the ground and then during the
flight test. In any engine in standard engine working conditions, all parameters should stay in the
range indicated in the table.
Operating Limits
Min
Max
Normal
Max difference
between bank
Reference
T refrigerant [°C]
72
102
87
5
Q.8.6.
T engine oil [°C]
50
120
100
---
Q.9.5.
T Gear box oil [°C]
20
100
60
---
Q.14.5.
T fuel [°C]
---
48
35
---
Q.10.7.
T air intake manifold [°C]
0
70
25
2
Q.11.4.
T ECU [°C]
-20
80
35
---
Q.12.3.
T voltage regulator [°C]
-20
75
55
---
Q.11.4.
P engine oil [bar]
0.05
2.0
1.5
---
Q.9.5.
P fuel [bar]
2.9
3.6
3.4
---
Q.10.7.
Q.4.6.1.C
Avoid any installation that causes engine overheating. An excess of the value
indicated in the table Q.4.6.1.C can cause a damage or stoppage of the engine.
Take note: if for any reasons, during flight, operating on the ground or just
after turning off the engine, if the ECU temperature exceeds the value
indicated in table Q.6.4.1.C, the ECU could be damaged and it is mandatory to
send it to an MW Fly service center for control.
The cooling system must be designed to guarantee that the engine will work at a
temperature that is lower than the max temperature indicate in the table Q.6.4.1.C
in any operating condition. When the engine is operated outside of the parameter
range indicated in the table Q.6.4.1.C the engine guarantee will be null and void
and this will release engine manufacturer from any liability.

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Q.5. PREPARING FOR INSTALLATION
The shipping crate bolts and screws must not be used to attach engine to the
airframe.
Start up the engine only when the installation is completed and with the propeller
mounted. Not respecting this procedure can cause serious damage to the engine.
In case of a prolonged period of storage before installation (over 12 month), it is
necessary to carry out all required checks and operations as described in section
B.8.2.
Q.5.1. Engine handling
Pay attention while moving the engine, use caution to prevent injuries and material
damage.
RAM
INTA KE
EFFECT
E
C
L
P
E
K
E
Y
D
N
A
D
R
FL Y
A
N
Q.5.1.1.P
To lift the engine MW Fly has designed a
special hook (code X285). The hook is wedged
in the propeller flange and fixed to a through
hole at the top/front engine casing with an
M8x55 mm bolt. Lift the engine from the shaft
indicated by the arrows on the special tool
X285 as shown in the picture Q.5.1.1.P. The
position of the shaft is in line with the center of
gravity, the propeller axis will be almost
horizontal.
In case the X285 hook is not available, it is possible to lift the engine using a rope around the
propeller shaft and the top rear mounting point.
The rope should be long enough to pass over the intake manifolds to avoid damage.

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Q.6. ENGINE POSITION AND ATTACHMENT
Q.6.1. Assembly position
The B22 engine must be fitted on the fuselage with the propeller axis horizontal or slightly
inclined, only a small deviation is permitted. In all cases the engine sump must remain at the
bottom.
B 22 AeroPower can be used on both a traction application and a pushing
application.
Make sure that no part of the aircraft touches or can accidentally touch the
engine hot parts (pay particular attention to the area around the exhaust
system).
To counteract the lateral force generated by the LEFT rotating propeller it will be necessary to
incline the horizontal axis of the engine by 2 degrees (general rule) to have a satisfactory result.
Ideal deviation on a vertical axis is such that the propeller axis will be above the CoG by 15/20
cm. Normally this angle is close to 0 or can be out by 1 to 2 degrees in a nose down
configuration.
To attain good lubrication the engine angles must never exceed data reported in next paragraph.
Check the angles on the ground and in flight.
The layout of the two cylinder heads with reference to the horizontal line is 0 deg. In case of the
specific need where one cylinder head is positioned lower than the other do not exceed the data
specified in table Q.6.1.1.C or Q.6.1.2.C. This is to avoid excessive oil build up in the lower
cylinder head.
Q.6.1.1. Permitted deviation angles
The symbol – placed before pitch angle denotes a propeller angle below the horizontal line, the
symbol + on the upper side.
The table below refers to an engine used on a tractor configuration only.
Application in tractor cofiguration
Rotation Angle [deg] applied to:
On ground
In flight
Pitch axis
+8/-3
+45/-10
Bank angle
+5/-5
+45/-45
Q.6.1.1.C
Exceeding deviation angles specified above can cause great danger.
Never position the engine in a manner different from the one prescribed
above.
All engines are supplied in TRACTOR configuration, unless specified on purchase order. To use
them in a pusher configuration the engine sump and oil strainer ( code T160) must be replaced
allowing oil pick up to operate in the opposite direction.
In this instance max rotation angle will be the following:

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Pusher application
Rotation angle [deg] applied to:
On ground
In flight
Pitch axis
+3/-8
+10/-40
Bank angle
+5/-5
+45/-45
Q.6.1.2.C
Q.6.2. Description of the mounting points
Built into the engine, there are nine mounting points. In a standard wall installation the mounting
points are on the rear side labeled “R”. For standard bed installation use the four lower
attachment points labeled “L”. When utilizing the “L” mounting point it is mandatory to use the
special adapter (code S039). A combination of “L” and “R” attachment points can also be used to
install the engine into the airframe. Both the “R” attachment points and the S039 adapter are
machined to house the rubber dampers. The engine is supplied with its own dampers, 4 red
(hardness 45sh) and 4 black (hardness 70sh). Dampers with a hardness of 60sh and 80sh are
optional.
On the front top part of the engine, labeled with an “F” there is an additional attachment point.
The “F” attachment point should be used in combination with at least two “R” or two “L”
attachment points. Using the “F” attachment point it is mandatory to use a damping element
between the engine and the engine frame.
The coordinates of the attachment points are indicated in the following tables.
Version without gear box
Axis on wall attachment point
[mm]
R1 Point
R2 Point
R3 Point
R4 Point
X
544
544
544
544
Y
100
137.5
-100
-137.5
Z
-135.2
164.8
-135.2
164.8
Q.6.2.1.C
Version without gear box
Axis on bed attachment point
[mm]
L1 Point
L2 Point
L3 Point
L4 Point
X
150
463.4
150
463.4
Y
98
98
-98
-98
Z
-155.2
-155.2
-155.2
-155.2
Q.6.2.2.C
Version without gear box
Axis on front top attachment point
[mm]
F Point
X
203.5
Y
± 20
Z
173.6
Q.6.2.3.C