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WT9 Dynamic LSA. AIRCRAFT MAINTENANCE MANUAL (AS-AMM-01-000, 22. 05. 2017) - page 14

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ELECTRICAL
POWER

Fig. 24-2

Simplified Schematic Diagram (Towing Version)

DC GENERATION

ELECTRICAL

POWER

24-30 DC GENERATION

1. DESCRIPTION

Generator system

The generator system consists of the following components:

•

Generator

•

Voltage regulator

•

Charging fuse

•

Low voltage warning light

The maintenance free AC generator is integrated into the engine and supplies
power to the equipment during normal operation.

The generated AC voltage is rectified and regulated by the voltage regulator.
The voltage regulator and charging fuse are installed on the firewall in the engine
compartment.

The low voltage warning light

CHARGE

is located on the left instrument panel

(Chapter 39-10).

Battery

The lead acid maintenance free battery 12 V / 17 Ah or 12V / 20 Ah battery is
installed in the engine compartment at the firewall; supplies power to the starter
and is also used as an emergency power supply when the engine has stopped.

SV-BAT-320 backup battery

SkyView displays have the SV-BAT-320 external backup batteries. In the event
of an electrical failure that causes SkyView to run on the SV-BAT-320,
the SV-BAT-320 supplies power to the SkyView display it is connected to, along
with any connected SV-ADAHRS-200, SV-EMS-220, and SV-GPS-250 module.
A fully charged SV-BAT-320 can keep most SkyView systems operating
for at least 45 minutes.

NOTE

Refer to “Dynon Avionics SkyView System Installation, Document
101320-

022, Revision Q” or later for additional information.

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2. MAINTENANCE PRACTICES

Generator

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

Voltage regulator

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 13

2 pcs

Persons

Tab. 24-1 Recommended tools, materials, persons and documentation

WARNING

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

(1) Voltage regulator removal:

(a) Make sure that the

IGNITION

switches are set to

OFF

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

(d) Disconnect the connector (7, Fig. 24-3) from the regulator (1).

(e) Remove the mounting nuts (3), washers (4, 5), ground wire (6) and

bolts (2).

(f)

Remove the regulator (1).

(2) Voltage regulator installation

(a) Make sure that the

IGNITION

switches are set to

OFF

(b) Put the regulator (1, Fig. 24-3) in position on the firewall (8).

wire (6) and nuts (3).

(d) Connect the connector (7) to the regulator (1).

(e) Check if regulator is firmly secured.

(f)

Connect the battery.

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

(h) Carry out an operational test; check function.

DC GENERATION

ELECTRICAL

POWER

– Voltage regulator

– Washer Ø6.4 x 12 x 1.6

– Bolt M6 x 25

– Ground wire

– Self-locking nut M6

7 - Connector

– Washer

6.4 x 18 x 1.6

– Firewall

Fig. 24-3 Voltage Regulator Removal / Installation

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Battery

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 7

1 pc

Wrench 8

1 pc

Persons

Tab. 24-2 Recommended tools, materials, persons and documentation

(1) Battery removal:

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

(b) Unscrew the bolt (6, Fig. 24-4), remove washers (8; 9) and cover (3).

the nut (11), removing the washers (7) and the bolt (4).

(d) Perform same procedure with wires (15) on positive terminal (14).

(e) Unscrew the nut (11) and remove the washers (7; 10) and the bolt (5),

open holder (16) and remove the battery (1).

(f)

Pull out the battery from Econet casing (2).

(2) Battery installation:

(a) Put the battery (1, Fig. 24-4) to the Econet casing (2).

(b) Open holder (16), insert battery (1) and attach it by means of the bolt

(5), washers (7; 10) and nut (11).

(4), washers (7) and nut (11).

(d) Perform same procedure with wires (12) on negative terminal (13).

(e) Install cover (3) and attach it by means of the bolt (6) and washers

(8; 9).

(f)

Install the engine cowlings (Chapter 71-10).

DC GENERATION

ELECTRICAL

POWER

Fig. 24-4 Battery Removal / Installation (page 1 of 2)

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– Battery

– Washer

6.4 x 20 x 6

– Econet casing

– Self-locking nut M5

– Cover

– Wires (-)

– Bolt M5x15

– Negative terminal

– Bolt M5x18

– Positive terminal

– Bolt M4x10

– Wires (+)

– Washer

5.3 x 15 x 1.2

For information:

– Washer

4.3 x 12 x 1

– Battery holder

– Spring locking washer

4.3

Fig. 24-4 Battery Removal / Installation (page 2 of 2)

SV-BAT-320 backup battery

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 7

1 pc

Screwdriver

1 pc

Philips screwdriver

1 pc

Persons

Tab. 24-3 Recommended tools, materials, persons and documentation

NOTE

Described is procedure for removal/installation of backup battery
on the left instrument floor. The procedure for backup battery
on the right instrument floor is analogous.

(1) Backup battery removal:

(a) Remove the instrument panel cover (Chapter 39-10).

(b) Disconnect the connector (3, Fig. 24-5) from the backup battery (1; 2).

(d) Remove the backup battery (1; 2) from the instrument floor (7, 8).

(2) Backup battery installation:

(a) Put the backup battery (1; 2, Fig. 24-5) in position on the instrument

floor (7; 8).

(b) Hold the battery and attach it with bolts (4), washers (6) and nuts (5).

(d) Install the instrument panel cover (Chapter 39-10).

(e) Carry out an operational test (see Dynon Avionics SkyView System

Installation, Document 101320-

022, Revision Q” or later).

DC GENERATION

ELECTRICAL

POWER

– Left backup battery

– Washer

4.3 x 12 x 1

– Right backup battery

For information:

– Connector

– Left instrument floor

– Bolt M4 x 12

– Right instrument floor

– Self-locking nut M4

Fig. 24-5 SV-BAT-320 Backup Battery Removal / Installation

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ELECTRICAL
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EXTERNAL POWER

ELECTRICAL

POWER

24-40 EXTERNAL POWER

1. DESCRIPTION

The  aircraft  is  equipped  with  the  external  power  source  socket,  which  is  located
in  the  left  side  of  the  cabin,  bellow  the  instrument  panel.  External  power  source
is  intended  for  engine  starting,  maintenance  procedures  requiring  reliable  power
for an extended period and for battery charging.

Recommended power source output is:

Shortly for engine start:

Max. 12 V / 90 A DC

For maintenance purposes:

Max. 12 V / 25 A DC

2. MAINTENANCE PRACTICES

External power socket

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

Pads (various thickness)

Spirit level

1 pc

Persons

Tab. 24-4 Recommended tools, materials, persons and documentation

(1) External power socket removal:

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

(b) Disconnect the battery and cables (5, Fig. 24-6).

(d) Unscrew the nuts (3), remove washers (4), bolts (2) and remove

the external power socket (1) with cables (5).

(2) External power socket installation:

(a) Put the external power socket (1, Fig. 24-6) in position on the bracket

(6).

(b) Attach the socket (1) with bolts (2), washers (4), and nuts (3).

(d) Connect the cables (5) and battery.

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

(f)

Carry out an operational test; check function.

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– External power socket

– Cable

– Bolt M5 x 18

For information:

– Self-locking nut M5

– Bracket

– Washer

5.3 x 15 x 1.2

Fig. 24-6 External Power Socket Removal / Installation

DC ELECTRICAL LOAD DISTRIBUTION

ELECTRICAL

POWER

24-60 DC ELECTRICAL LOAD DISTRIBUTION

1. DESCRIPTION

The electrical power from the generator and the battery is supplied via 12 V bus,
switches and circuit breakers to the individual electrical equipment.
Switches are installed at the lower edge of instrument panel’s left side.
Circuit breakers are located at the lower and right side of instrument panel’s right side.
Circuit breaker

’s marking and values are listed in the Table 24-5.

Dual contactless ignition of the engine it is a separate part of electrical installation.
Each ignition circuit can be switched off independently using corresponding

IGNITION

switch

(see

Chapter

74-30).

Keyed

ignition

switch

connected

to the battery through a

MASTER SWITCH

. It has positions

OFF

INST.

CHARGE

START

. In the

OFF

position, the starter is electrically isolated. In the

INST.

position

are energized single value instruments (engine hours and flight hours) and fuel pump.
In the

CHARGE

position also a warning lamp

CHARGE

is energized and indicates

the charging status. In the

START

position, the starter is energized and will

automatically return to the position

CHARGE

when released.

PFD and MFD displays Dynon SkyView SV-D1000 are connected through

LH D1000

and

LH D1000

circuit breakers directly to the

MASTER SWITCH

Avionics (RDST, XPDR, intercom and traffic sensor) are connected through separate

COMM

NAV

XPDR,

INTERCOM

and

TIS

circuit breakers to the avionic relay. Avionic

relay is activated by separate

AVIONICS

switch and is protected by

AVIONICS

circuit

breaker that is connected to the

MASTER SWITCH

Navigation and anti-collision lights are activated by

NAV / ACL

switch and are

connected through

NAV / ACL

circuit breaker to the

MASTER SWITCH

. Landing lights

are activated by

LAND

switch and are connected through

LAND

circuit breaker

to the

MASTER SWITCH

Fuel pump is activated by separate

FUEL PUMP

switch and is connected through

FUEL PUMP

circuit breaker to the

INST.

position of keyed ignition switch.

Stall warning system consists of  stick shaker handle, buzzer and warning lamp that
are  triggered  by ACI Stall  Warner  (AoA flap)  and  Stall  Warning  Transducer  (buzzer
and  warning  lamp  only).  Stall  warning  system  is  connected  through

STALL

circuit

breaker to the

MASTER SWITCH

Function of warning lamps, control lamps, stick shaker and stall warning horn can be
verified by pressing button labelled

TEST

Pitch and roll trim actuators are activated by separate switches and are connected
through

PITCH

and

ROLL

circuit breakers to the

MASTER SWITCH

Low oil pressure warning circuit and low fuel level warning circuit have a separate

OIL

PRESS.

and

FUEL RES.

circuit breakers.

12 V sockets of an automotive type are installed at the both lower corners of instrument
panel and are connected through

SOC. 12V

circuit breaker to the

MASTER SWITCH

Engine hours and flight hours are supplied through

SVI

circuit breaker from the

INST.

position of keyed ignition switch.

ELT has its own battery for power supply.

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Towing version:

Camera is activated by

CAMERA

switch and is connected through

CAMERA

circuit

breaker to the

MASTER SWITCH

Propeller is regulated by a propeller regulator and is connected through

PROPELLER

circuit breaker to the

MASTER SWITCH

NO. MARKING

PROTECTED INSTRUMENT

VALUE (A)

PITCH*

Pitch trim actuator

7.5

ROLL*

Roll trim actuator

STALL*

Stall warning system

AVIONICS

Avionics relay

FUEL PUMP

Fuel pump

COMM

GNC 255A (COMM)

XPDR

GTX 328

GTX 335

LH D1000

LH Dynon SkyView SV-D1000

RH D1000

RH Dynon SkyView SV-D1000

10.

OIL PRESS.

Low oil pressure warning

11.

FUEL RES.

Low fuel level warning

12.

SOC. 12V

LH and RH socket 12V

13.

SVI

Engine hours counter Hobbs
Flight hours counter Winter FSMZ
RPM indicator ROAD IF61.2B35.2301

14.

TIS

TRX-1500

AT-1

15.

SPARE

16.

NAV / ACL

Anti-collision lights

17.

LAND

Landing lights

18.

NAV

GNC 255A (NAV)

19.

INTERCOM

PM3000

20.

CAMERA

Camera (towing version)

21.

PROPELLER*

Propeller regulator (towing version)

Tab. 24-5 Circuit breakers rating

NOTE

*KLIXON 7277-2 circuit breakers are used in pitch trim, roll trim, stall
warning system and propeller circuits. Remaining circuits are protected
by ETA 106-P10 circuit breakers.

DC ELECTRICAL LOAD DISTRIBUTION

ELECTRICAL

POWER

2. MAINTENANCE PRACTICES

12 V socket

For removal / installation, see the Chapter 39-10.

ETA 106-P10 circuit breakers

For removal / installation, see the Chapter 39-10.

KLIXON 7277-2 circuit breakers

For removal / installation, see the Chapter 39-10.

Switches

For removal / installation, see the Chapter 39-10.