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

AIR INTAKES

POWER PLANT

- GENERAL

–

Cable end fitting

–

Green sleeve

–

Thread rod

–

Low nut M10

–

Low nut M6

–

Serrated locking washer

10.5

–

Washer

6.4x 18 x 1.2

–

Handle

–

Screw shackle

–

Low nut M5

–

Lockwire

0.8

For information:

–

Control cable

–

Central console

–

Bowden end

–

Firewall

–

Cable tie 2.6

18 - Air filter holder bellcrank

–

Textile adhesive tape

Fig. 71-12 Carburettor Pre-Heat Control Removal / Installation

ENGINE DRAINS

POWER PLANT

- GENERAL

71-70

ENGINE DRAINS

1. DESCRIPTION

The engine installed in the aircraft has the following engine drains and venting
(see Fig. 71-13):

•

Airbox drain.

•

Drip tray drain.

•

Fuel drain from the fuel pump.

•

Oil tank venting (Chapter 79).

•

Carburettors float chamber venting.

All drains consist of the rubber hoses. Hoses from each drip tray and airbox connect
to a Y piece connector. From the Y piece connector, the drain hose leads to the bottom
of the firewall. All hoses discharges bellow the fuselage into the slipstream.

–

arburettor’s

float chamber venting 4

–

Drip tray drain

–

Airbox drain

–

Fuel pump drain

–

Drip tray

–

Oil tank venting

Fig. 71-13 Engine Drains

Effectivity:

ALL

28. 04. 2021

POWER PLANT
- GENERAL

2. MAINTENANCE PRACTICES

A. Drains

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

Screwdriver 2

1 pc

Wire nippers

1 pc

Cable tie 2.6

Cable tie 4.8

Persons

Tab. 71-7 Recommended tools, materials, persons and documentation

WARNING

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

(1) Drains removal:

(a) Make sure that the

IGNITION

switches are set to

OFF

(b)  Remove the engine cowlings (Chapter 71-10).
(c)  Disconnect negative terminal of battery (Chapter 24-30).
(d)  Remove  all  cable  ties  (10,  Fig.  71-14)  on  length  of  drain  hoses

(1; 2; 3; 4; 5; 6) and safety clamps (8; 9).

(e) Disconnect and remove drain hoses.

(2) Drains installation:

(a) Make sure that the

IGNITION

switches are set to

OFF

(b) Route the drain hoses (1; 2; 3; 4; 5; 6, Fig. 71-14).
(c) Connect drain hoses with 3-way distributors (7) and secure drain

hoses with cable ties (10) and safety clamps (8; 9).

(d) Secure drain hoses (3, 4) with necessary amount of cable ties.
(e) Check if all hoses are well secured.
(f)

Install the engine cowlings (Chapter 71-10).

ENGINE DRAINS

POWER PLANT

- GENERAL

–

Draining hose

–

N/A

–

Draining hose

–

Safety clamp 10.9

–

Draining hose

–

Cable tie 2.6

–

Draining hose

–

Holder

–

Draining hose

–

Bolt

3x10

–

Draining hose

–

Hose clamp

ø20

- 32

–

3-way distributor

–

Cable tie 4.8

Fig. 71-14 Engine Drains

GENERAL

ENGINE -

FUEL AND CONTROL

73-00 GENERAL

1. INTRODUCTION

This chapter describes those units and components which deliver metered fuel
to the engine. Components covered the standby fuel pressure indicator, fuel pressure
sensor and fuel flow transducer that part of aircraft manufacturer installation.

Fuel is supplied to the engine in dependence from

FUEL

selector valve position

(

LEFT

RIGHT

OFF

). From both fuel tanks the fuel flows through the fuel filters

to the

FUEL

selector valve inlets. From the

FUEL

selector valve the fuel flows

through the electric fuel pump (by-passed with check valve) to engine driven fuel
pump and then to distributor inlet.

One of distributor's outlets is connected to carburettors through the fuel flow meter
sensor and 3-way distributor. Second one is fitted with restrictor jet to which return
line is connected. Return line leads back to the left fuel tank.

Fuel flow transducer is installed the way to measure only the fuel consumed
by engine. For installation of fuel flow transducer see Chapter 28-40.

Fuel  pressure  sensor  and  standby  fuel  pressure  indicator  are  installed  in  the  fuel
system and  connected  through  the  3-way  distributor  with  restrictor  jets  in  its  outlets
to  the  4-way  distributor.  Both  check  the  actual  pressure  in  the  fuel  supply  line.
For  installation  of  fuel  pressure  sensor  see  Chapter  28-40.  For  installation  of  fuel
pressure indicator see Chapter 39-10.

Scheme of fuel system is stated in Chapter 28.

Wiring diagram of fuel pressure sensor and fuel flow transducer is described
in the Aircraft Wiring Manual (Doc. No. AS-AWM-01-000).

Effectivity:

ALL

12. 06. 2020

ENGINE -
FUEL AND CONTROL

2. TROUBLESHOOTING

TROUBLE

POSSIBLE CAUSE

REMEDY

Insufficient fuel pressure.

Clogged strainer.

Clean strainer.

Defective mechanical fuel
pump.

Replace fuel pump.

Defective fuel pressure
sensor.

Replace the fuel pressure
sensor.

Wrong fuel pressure
sensor set up in Dynon
Skyview.

Set up correctly fuel
pressure sensor in Dynon
SkyView.

Defective fuel pressure
indicator.

Replace the fuel pressure
indicator.

No fuel pressure
indication

Defective fuel pressure
sensor.

Replace the fuel pressure
sensor.

Faulty or incorrect fuel
pressure sensor wiring.

Repair/Replace wire(s).

Fluctuating fuel flow
indications.

Defective fuel flow
indicator/transducer.

Replace fuel flow
indicator/transducer

Vapor in fuel lines.

Turn on electric fuel
pump.

GENERAL

IGNITION

74-00 GENERAL

1. INTRODUCTION

This chapter describes those units and components which furnish, distribute, and
control an electrical current to ignite the fuel-air mixture in the engine cylinders. The
ignition components include coils, electronic modules, ignition harness, spark plugs,
and ignition switches.

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

Effectivity:

ALL

22. 05. 2017

IGNITION

2. TROUBLESHOOTING

TROUBLE

POSSIBLE CAUSE

REMEDY

Engine does not start/not
easy to start.

Ignition switch/switch
cable defective.

Carry out the ignition
switch test.
If necessary replace the
ignition switch or ignition
switch cables.

Defective ignition spark-
plug leads.

Replace the spark-plug
leads.

Low battery voltage.

Charge / replace battery.

Fouled spark plugs.

Clean spark plugs
according to
manufacturer’s
specifications.

Incorrect spark plug gap.

Re-gap spark plugs to
engine manufacturer’s
specifications.

Rough running.

Fouled spark plugs.

Clean spark plugs
according to
manufacturer’s
specifications.

Incorrect spark plug gap.

Re-gap spark plugs to
engine manufacturer’s
specifications.

Ignition switch/switch
cable defective.

Carry out the ignition
switch test.
If necessary replace the
ignition switch or ignition
switch cables.

Excessive RPM drop
during ignition test.

Fouled spark plugs.

Clean spark plugs
according to
manufacturer’s
specifications.

Incorrect spark plug gap.

Re-gap spark plugs to
engine manufacturer’s
specifications.

Faulty spark plug.

Test spark plug in
accordance with
manufacture’s
specifications.

ELECTRICAL POWER SUPPLY

IGNITION

74-10 ELECTRICAL POWER SUPPLY

1. DESCRIPTION

The engine Rotax 912 ULS2 engine is equipped with a dual ignition unit of a
breakerless, capacitor discharge design, with an integrated generator
(Chapter 24-10).

The ignition unit needs no external power supply.

Two independent charging coils (1) located on the generator stator supply one
ignition circuit each. The energy is stored in capacitors of the electronic modules
(2, Fig. 74-1). At the moment of ignition 2 each of the 4 external trigger coils (3)
actuate the discharge of the capacitors via the primary circuit of the ignition coils (4).
The trigger coil (5) is provided for rpm indicator signal (Chapter 39-10).

– Charging coils

– Dual ignition coils

– Electronic modules

– Trigger coils for speed signal

– Trigger coils for ignition signal

Fig. 74-1 Ignition System

Effectivity:

ALL

22. 05. 2017

IGNITION

Firing order: 1-4-2-3 (see Fig. 74-2).

Fig. 74-2 Firing Order

2. MAINTENANCE PRACTICES

Refer to the Maintenance Manual for Engine Type 912 Series, Ref. No.: MML-912 for
maintenance practices information.

DISTRIBUTION

IGNITION

74-20 DISTRIBUTION

1. DESCRIPTION

This chapter describes that portion of the ignition system which conducts high-
voltage electricity from the electronic modules to the spark plugs. Shielded leads
connect the electronic modules to the spark plugs.

Two spark plugs in each cylinder give ignition to the engine. Ignition circuit A controls
top spark plugs of cylinder 1 and 2; lower spark plugs of cylinder 3 and 4. Ignition
circuit B controls top spark plugs of cylinder 3 and 4; lower spark plugs of cylinder 1
and 2.

2. MAINTENANCE PRACTICES

Refer to the Maintenance Manual for Engine Type 912 Series, Ref. No.: MML-912 for
maintenance practices information.

SWITCHING

IGNITION

74-30 SWITCHING

1. DESCRIPTION

Ignition circuits are controlled independently by switches on the instrument panel
labelled

IGNITION

. The left switch controls the ignition circuit A; the right switch

controls the ignition circuit B. Starter is controlled by a keyed ignition switch installed
in the instrument panel. Keyed ignition switch is labeled clockwise:



OFF

Off-state.



INST.

Instrument connection.



CHARGE

Charging.



START

The starter is energized and will crank the engine, when the key is

released, it will automatically return to the

CHARGE

position.

Activation of the ignition circuit A and ignition circuit B is signalized on the SV-D1000
EMS screen (Chapter 77-00).

– Left ignition circuit switch

– Keyed ignition switch

– Right ignition circuit switch

Fig. 74-3 Ignition Controls

Effectivity:

ALL

22. 05. 2017

IGNITION

2. MAINTENANCE PRACTICES

Ignition switches

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

Keyed ignition switch

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

WT9 Dynamic LSA. AIRCRAFT MAINTENANCE MANUAL (AS-AMM-01-000, 22. 05. 2017) - page 41