WT9 Dynamic LSA. AIRCRAFT MAINTENANCE MANUAL (AS-AMM-01-000, 22. 05. 2017)

Effectivity:

ALL

24. 11. 2020

ENGINE
CONTROLS

(f)

Put bowdens (18; 19) onto inner cables (20) and route them through
firewall and screw shackle to carburetors.

(g) Secure bowdens (18; 19) with lockwire (7) to leading bracket (17) and

the screw shackle.

(h) Cover bowdens (18; 19) with spiral hoses (10) in engine compartment.

(i)

Secure control cables along length with necessary amount of cable
ties (4.8 mm).

(j)

Adjust

THROTTLE

controller (see 2.A.(3)).

(3)

THROTTLE

controller adjusting:

(a) Push

THROTTLE

controller fully in and then pull out for 4 mm.

(b) Connect inner cable (20, Fig. 76-3) with throttle lever through

perforated screw (25), strain inner cable (20) at 30 N and tighten
the nut (24).

(d) Connect and adjust second inner cable.

(e) Carry out test and check:

•

If all screw connections are tight.

•

Operating of throttle.

•

That no foreign objects remain in the aircraft.

(f)

Install the airbox (Chapter 71-60).

(g) Install the engine cowlings (Chapter 71-10).

POWER CONTROL

ENGINE

CONTROLS

– Handle

14b

–

THROTTLE

controller 2

– Cover nut

– Ring

– Serrated locking washer ø10

– Hose clamp ø16 - 27

– Nut M10

– Leading bracket

–

CHOKE

controller

– Right bowden

– Hex head bolt M4 x 5

– Left bowden

– Lockwire ø0.8 mm

–

THROTTLE

controller’s inner cable

– Right bowden

– Spring

– Left bowden

–

CHOKE

controller

’s inner cable

– Spiral hose ø6

– Hex head bolt

– Distance tube

– Self-locking nut

– Serrated locking washer ø19

– Perforated screw

– Nut M19

For information:

14a

–

THROTTLE

controller 1

– Central console

Fig. 76-3 Throttle and Choke Controllers Removal / Installation

Effectivity:

ALL

24. 11. 2020

ENGINE
CONTROLS

Choke controller

Type of maintenance:

Heavy

Personnel qualification:

Independent certifying staff qualified in accordance

with Part-66 or higher.

Recommended tools, materials, persons and documentation:

ITEM

QUANTITY

Screwdriver 10

1 pc

Screwdriver 5

1 pc

Phillips screwdriver

1 pc

Hex key 2

1 pc

Hex key 3

1 pc

Hex key 4

1 pc

Wrench 8

1 pc

Wrench 9

1 pc

Wrench 17

2 pcs

Cable tie 2.6

Cable tie 4.8

Lockwire

ø0.8 mm

Loctite 243

Maintenance Manual (Line Maintenance) for Rotax Engine
Type 912 Series, Ref. No.: MML-912

Persons

Tab. 76-2 Recommended tools, materials, persons and documentation

WARNING

ENGINE IGNITION MUST BE SWITCHED OFF!

(1)

CHOKE

controller removal:

(a) Make sure that the

IGNITION

switches are set to

OFF

(b) Remove the engine cowlings (Chapter 71-10).

(d) On carburetors, release the hex head bolts (23, Fig. 76-3) and

disconnect choke´s inner cables (22).

(e) Remove lockwire (7) and remove the spiral hoses (10).

(f)

Behind central instrument panel, remove lockwire (7) and pull out
the bowdens (8; 9), coil the inner cables (22).

(g) Unscrew choke handle (1).

(h) Unscrew the nut (2) and remove the

CHOKE

controller (5).

POWER CONTROL

ENGINE

CONTROLS

(2)

CHOKE

controller installation:

(a) Secure the bolts (6, Fig. 76-3) with Loctite 243.

(b) Behind the central console (26) slide the choke (5) with the nut (4) and

the washer (3).

(2) and then tighten the nut (4).

(d) Screw the handle (1) secured with Loctite 243.

(e) Slide bowdens (8; 9) on inner cables (22) and secure them

with lockwire (7).

(f)

Direct the bowdens with inner cables (22) through firewall and band
tubes to choke levers on carburetors.

(g) Cover bowdens (8; 9) with the spiral hoses (10) in engine compartment

and secure bowdens (8; 9) with lockwire (7) to band tube.

(h) Secure control cables along length with necessary amount of cable

ties (4.8 mm).

(i)

Adjust

CHOKE

controller (see 2.B. (3)).

(3)

CHOKE

controller adjusting:

(a) Pull choke handle to open position (approximate 20 mm).

(b) At carburetors disconnect the springs (21, Fig. 76-3), turn up choke

lever (open choke).

with Loctite 243.

(d) Cut unnecessary inner cable and solder the ends.

(e) Put on the springs (21) back.

(f)

Connect and adjust second inner cable.

(g) Carry out test and check:

•

If all screw connections are tight.

•

Operating of choke.

•

That no foreign objects remain in the aircraft.

(h) Install the airbox (Chapter 71-60).

(i)

Install the engine cowlings (Chapter 71-10).

GENERAL

ENGINE

INDICATING

77-00 GENERAL

1. INTRODUCTION

This chapter describes those components that indicate engine operation.

Engine instruments function fulfils the SV-D1000 EMS multifunction display
of the Dynon SkyView system.

The sensors that sense the engine parameters, transmits the information to the
SV-EMS-220 module. Information after processing is sent to the SV-D1000 EMS.

The SV-EMS-220 Module provides the interface between the SV-D1000 EMS and
the engine sensors. It allows the SkyView System to continuously monitor all power
plant systems in a highly automated manner. Any parameter falling outside its
predefined limits are automatically brought to the attention of the pilot for immediate
remediation.

Following engine parameters are displayed on the screen of SV-D1000 EMS
(see Fig. 77-1):

•

Engine RPM

•

Coolant temperature

•

EGT temperature

•

Airbox temperature

•

Oil temperature (Chapter 79-30)

•

Oil pressure (Chapter 79-30)

•

Manifold pressure

•

Current

•

Voltage

Exceeding of engine parameters is signalized with the

EMS

warning lamp

(Chapter 31-50).

In case of SV-EMS-220 module failure, the engine rpm are displayed by standby
RPM indicator or propeller regulator (towing version).

NOTE

Refer to “Dynon Avionics SkyView System Installation, Document 101320-022,
Revision Q” or later for additional information.

GENERAL

ENGINE

INDICATING

2. TROUBLESHOOTING

TROUBLE

POSSIBLE CAUSE

REMEDY

No RPM indication.

Defective RPM indicator.

Replace the RPM
indicator.

Incorrect RPM indication.

Defective RPM indicator.

Replace the RPM
indicator.

No coolant temperature
indication.

Defective coolant sensor.

Replace the sensor.

Defective electrical cable.

Repair the defective
electrical cable.

Defective coolant
temperature indicator.

Replace the defective
coolant temperature
indicator.

High coolant temperature
indication.

Defective engine.

Refer to the Rotax
Maintenance Manual.

Defective coolant
temperature indicator.

Replace the defective
coolant temperature
indicator.

No exhaust gas
temperature indication.

Defective EGT sensor.

Replace the EGT sensor.

Defective electrical cable.

Repair the defective
electrical cable.

Defective EGT indicator.

Replace the defective
EGT indicator.

High exhaust gas
temperature indication.

Defective engine.

Refer to the Rotax
Maintenance Manual.

Defective EGT indicator.

Replace the defective
EGT indicator.

POWER

ENGINE

INDICATING

77-10 POWER

1. DESCRIPTION

This section describes that portion of the engine indicating system which indicates
the engine power. Included are the RPM indicating components and MAP indicating
components.

The generator trigger coil is provided for RPM indicator signal. Signal from the coil is
carried to the engine monitoring system unit Dynon EMS 220 and from there to the
Dynon SkyView SV-D1000.

The MAP sensor is attached on the firewall in the engine compartment.

SV-EMS-220 Module is located in front of the instrument panel on the left instrument
floor.

On the centre section of the instrument panel is mounted standby RPM indicator
ROAD IF61.2B35.2301 or propeller regulator Flybox PR1-P (towing version).

Wiring diagram of engine parameters indicating is described in the Aircraft Wiring
Manual (Doc. No. AS-AWM-01-000).

2. MAINTENANCE PRACTICES

SV-D1000 display

For removal / installation procedures refer to Chapter 39-10.

SV-EMS-220 module

For removal / installation procedures refer to Chapter 77-40.

Standby RPM indicator

For removal / installation procedures refer to Chapter 39-10.

Propeller regulator Flybox PR1-P

For removal / installation procedures refer to Chapter 39-10.

MAP sensor

For removal / installation procedures refer to Chapter 77-40.

ENGINE SENSORS

ENGINE

INDICATING

77-40 ENGINE SENSORS

1. DESCRIPTION

This section describes that portion of the engine indicating system which indicates
engine parameters:

•

Coolant temperature

•

EGT temperature

•

Airbox temperature

•

Oil. temperature

•

Oil pressures

•

Manifold pressure

•

Current

Signal from the sensors is carried to the engine monitoring system unit Dynon EMS
220 and from there to the Dynon SkyView SV-D1000.

All the engine parameters are displayed on the SV-D1000 EMS.

Wiring diagram of engine sensors is described in the Aircraft Wiring Manual
(Doc. No. AS-AWM-01-000).

2. MAINTENANCE PRACTICES

Coolant temperature sensor

The coolant temperature sensor is screwed into the cylinder head No. 2.

Type of maintenance:

Line

Personnel qualification:

Independent certifying staff qualified in accordance

with Part-66 or higher.

Recommended tools, materials, persons and documentation:

ITEM

QUANTITY

Wrench 12

1 pc

Wrench 18

1 pc

Screwdriver 5

1 pc

Pliers

1 pc

Maintenance Manual (Line Maintenance) for Rotax Engine
Type 912 Series, Ref. No.: MML-912

Persons

Tab. 77-1 Recommended tools, materials, persons and documentation

WARNING

ALWAYS ALLOW ENGINE TO COOL DOWN TO AMBIENT
TEMPERATURE BEFORE START OF ANY WORK.

ENGINE IGNITION MUST BE SWITCHED OFF. DISCONNECT
NEGATIVE TERMINAL OF AIRCRAFT BATTERY.

Effectivity:

ALL

04. 07. 2019

ENGINE
INDICATING

(1) Coolant temperature sensor removal:

(a) Make sure that the

IGNITION

switches are set to

OFF

(b) Make sure that the

MASTER SWITCH

is set to

OFF

(d) Drain the coolant from the cooling system (Chapter 12-10).

(e) Disconnect negative terminal of battery (Chapter 24-30).

(f)

Disconnect wire (3, Fig. 77-2) from the sensor (1).

(g) Remove sensor (1) and ground wire (2) from the engine fitting.

(h) Install protective plug on the engine fitting.

(2) Coolant temperature sensor installation:

(a) Make sure that the

IGNITION

switches are set to

OFF

(b) Make sure that the

MASTER SWITCH

is set to

OFF

(d) Install sensor (1, Fig. 77-2) with ground wire (2) to the engine fitting.

(e) Connect wire (3) to the sensor (1).

(f)

Check if sensor is firmly secured and sealed.

(g) Replenish the cooling system (Chapter 12-10).

(h) Connect negative terminal of the battery (Chapter 24-30).

(i)

Carry out engine ground test; check cooling system for leaks and
coolant temperature indication.

(j)

Install the engine cowlings (Chapter 71-10).

Effectivity:

ALL

04. 07. 2019

ENGINE
INDICATING

EGT sensors

The EGT sensors are installed in the rear exhaust tubes.

Type of maintenance:

Line

Personnel qualification:

Independent certifying staff qualified in accordance

with Part-66 or higher.

Recommended tools, materials, persons and documentation:

ITEM

QUANTITY

Wrench 9

1 pc

Screwdriver

1 pc

Persons

Tab. 77-2 Recommended tools, materials, persons and documentation

WARNING

ENGINE IGNITION MUST BE SWITCHED OFF. DISCONNECT
NEGATIVE TERMINAL OF AIRCRAFT BATTERY.

MAKE SURE THE EXHAUST SYSTEM IS COOL BEFORE YOU
TOUCH IT. THE EXHAUST SYSTEM CAN BE HOT. THIS CAN
CAUSE INJURY TO PERSONS.

(1) EGT sensor removal:

(a) Make sure that the

IGNITION

switches are set to

OFF

(b) Make sure that the

MASTER SWITCH

is set to

OFF

(d) Disconnect negative terminal of battery (Chapter 24-30).

(e) Disconnect EGT sensor electrical cable.

(f)

Loose screw (2, Fig. 77-3) and disconnect EGT sensor (1) from
exhaust tube (3).

(g) Remove the sensor (1).

(2) EGT sensor installation:

(a) Make sure that the

IGNITION

switches are set to

OFF

(b) Make sure that the

MASTER SWITCH

is set to

OFF

(3); tighten the screw (2).

(d) Connect EGT sensor electrical cable.

(e) Check if sensor is firmly secured.

(f)

Connect negative terminal of the battery (Chapter 24-30).

(g) Carry out engine ground test; check EGT indication.

(h) Install the engine cowlings (Chapter 71-10).

Effectivity:

ALL

04. 07. 2019

ENGINE
INDICATING

Airbox temperature sensor

The airbox temperature sensor is screwed into the air filter holder.

Type of maintenance:

Line

Personnel qualification:

Independent certifying staff qualified in accordance

with Part-66 or higher.

Recommended tools, materials, persons and documentation:

ITEM

QUANTITY

Wrench 10

1 pc

Persons

Tab. 77-3 Recommended tools, materials, persons and documentation

(1) Airbox temperature sensor removal:

(a) Make sure that the

IGNITION

switches are set to

OFF

(b) Make sure that the

MASTER SWITCH

is set to

OFF

(d) Disconnect connectors (2; 3, Fig. 77-4) from each other.

(e) Unscrew sensor (1) and from air filter holder (4).

(f)

Install protective plug on the air filter holder fitting.

(2) Airbox temperature sensor installation:

(a) Make sure that the

IGNITION

switches are set to

OFF

(b) Make sure that the

MASTER SWITCH

is set to

OFF

(d) Install sensor (1, Fig. 77-4) to the fitting of air filter holder (4).

(e) Connect connectors (2; 3) together.

(f)

Check if sensor is firmly secured and sealed.

(g) Carry out engine ground test; check airbox temperature indication.

(h) Install the engine cowlings (Chapter 71-10).

ENGINE SENSORS

ENGINE

INDICATING

– Airbox temperature sensor

For information:

– Electrical connector

– Air filter holder

– Electrical connector

– Firewall

Fig. 77-4 Airbox Temperature Sensor Removal / Installation

WT9 Dynamic LSA. AIRCRAFT MAINTENANCE MANUAL (AS-AMM-01-000, 22. 05. 2017) - page 43