Content .. 24 25 26 27 ..

WT9 Dynamic LSA. AIRCRAFT MAINTENANCE MANUAL (AS-AMM-01-000, 22. 05. 2017) - page 26

STEERING

LANDING GEAR

Fig. 32-26 Steering Push Rods Removal / Installation (page 1 of 2)

Effectivity:

ALL

12. 06. 2020

LANDING GEAR

– Push rod

9 -

Washer ø6.4 x 12 x 1.6

– Push rod

10 -

Washer ø6.4 x 30 x 1.6

– Sleeve

11 -

Serrated locking washer ø6.4

– Sleeve flange

12 - Self-locking nut M6

– Bolt M6 x 25

13 - Nut M6

– Bolt M6 x 28

14 -

Hose clamp ø16-27

– Bolt M3 x 10

15 - Swivel bearing

8 -

Washer ø6.4 x 10 x 1

16 - Nose landing gear leg

Fig. 32-26 Steering Push Rods Removal / Installation (page 2 of 2)

GENERAL

LIGHTS

33-00 GENERAL

1. INTRODUCTION

This chapter describes the system and maintenance practices about the lighting on
the airplane.

Wiring diagram of the airplane lighting is described in the Airplane Wiring Manual
(Doc. No. AS-AWM-01-000).

Effectivity:

ALL

29. 01. 2020

LIGHTS

2. TROUBLESHOOTING

TROUBLE

POSSIBLE CAUSE

REMEDY

Both position lights do not
operate.

Circuit-breaker not set or
defective.

Set/replace the circuit-
breaker.

Defective position light
switch.

Replace the switch.

Defective wiring

Carry out a continuity test
of the wiring.
Repair/replace defective
wiring. Refer to Airplane
Wiring Manual (Doc. No.
AS-AWM-01-00)

One position light does
not operate.

Defective wiring.

Carry out a continuity test
of the wiring.
Repair/replace defective
wiring. Refer to Airplane
Wiring Manual (Doc. No.
AS-AWM-01-00).

Landing light not operate.

Defective light.

Replace the light.

Circuit-breaker not set or
defective.

Set/replace the circuit-
breaker.

Defective landing light
switch.

Replace the switch.

Defective wiring.

Carry out a continuity test
of the wiring.
Repair/replace defective
wiring. Refer to Airplane
Wiring Manual (Doc. No.
AS-AWM-01-000).

Loose connector next to
the light.

Connect the connector
correctly.

Decrease of light
transmission (milky
appearance)

Degradation of light cover
surface.

Polish with a good
automotive cleaner wax
and/or a liquid polishing
compound, apply coat of
an automotive polish and
polish with electric buffing
machine.

EXTERIOR LIGHTING

LIGHTS

33-40 EXTERIOR LIGHTING

1. DESCRIPTION

This chapter contains information on servicing the anti-collision / position and landing
lights. The anti-collision / position lights (1; 2, Fig. 33-1) are mounted to the outboard
surface of each wing tip. The light assembly includes a LED strobe light with forward
(red-left, green-right) and white position LED lights.

The landing lights (3) are mounted to the bottom engine cowl.

Landing lights are activated by switch labelled as

LAND

and they are connected

through a circuit breaker to the master switch. Anti-collision / position lights are
activated by switch labelled as

ACL/NAV

and they are connected through a circuit

breaker to the master switch.

–

Left anti-collision / position light (red)

–

Landing lights

–

Right anti-collision / position light (green)

Fig. 33-1 Exterior Lighting

Effectivity:

ALL

29. 01. 2020

LIGHTS

2. MAINTENANCE PRACTICES

Anti-collision / position lights

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

Phillips screwdriver

1 pc

Knife

1 pc

Soldering gun

1 pc

Cable tie 2.6

1 pc

Shrink tube

ø3.2 x 1.6

Persons

Tab. 33-1 Recommended tools, materials, persons and documentation

WARNING

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

(1) Anti-collision / position light removal:

(a) Remove wing (Chapter 57-10).

(b) On wing root remove cable tie and push wires into the wing.

(d) Pull out light (1), remove the spiral hose (5), remove shrink tubes and

unsolder the el. wires (4).

(e) Remove the light (1) and gasket (2).

(2) Anti-collision / position light installation:

(a) Shorten the wires (4, Fig. 33-2) of the light (1) to 100 mm.

(b) Pass the wires (4) through the appropriate hole in the gasket (2).

pull the shrink tubes over joints and apply heat to shrink them.

(d) Apply spiral hose (5) on joint. Set the position light (1) with the gasket

(2) to the wing tip (6) and fasten it with screws (3).

(e) Install wing (Chapter 57-10).

(f)

Carry out an operational test.

(3) Anti-collision / position light polishing:

(a) Polish the lights after installation.

NOTE

Under no circumstances should any petroleum based product be
used to clean the lights.

EXTERIOR LIGHTING

LIGHTS

– Anti-collision / position light

– Wires and shrink tubes (3 + 1)

– Gasket

– Spiral hose ø3

– Screw M3 x 20

– Wing tip

Fig. 33-2 Anti-collision / Position Light Removal / Installation

Effectivity:

ALL

04. 07. 2019

LIGHTS

Landing lights

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

Philips screwdriver

1 pc

Silicone

Persons

Tab. 33-2 Recommended tools, materials, persons and documentation

WARNING

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

NOTE

Removal / installation is the same for both landing lights.

(1) Landing light removal:

(a) Make sure that the

IGNITION

switches are set to

OFF

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

(d) Unscrew the screw (3), remove the washers (4; 5).

(e) Remove old silicone.

(f)

Pull out holder (2) and the landing light (1).

(2) Landing light installation:

(a) Clean all silicone residues.

(b) Make sure that the

IGNITION

switches are set to

OFF

(7).

(d) Insert the screw (3) with washers (4; 5) to the hole; tighten the screw.

(e) Connect the connector (6) to the light (1).

(f)

Install the engine cowlings (Chapter 71-10).

(g) Carry out an operational test.

EXTERIOR LIGHTING

LIGHTS

–

Landing light

–

Washer

ø4.3 x 12 x 1

–

Holder

–

Connector

–

Screw M4 x 10

For information:

–

Spring washer

ø4.3

–

Bottom engine cowl

Fig. 33-3 Landing Lights Removal / Installation

CONTENTS

NAVIGATION

34 NAVIGATION

CONTENTS

GENERAL ......................................................................... 3

INTRODUCTION ....................................................................... 3

34-10

FLIGHT ENVIRONMENTAL DATA ................................... 5

DESCRIPTION .......................................................................... 5

TROUBLESHOOTING ............................................................... 7

MAINTENANCE PRACTICES ................................................... 9

Pitot-static probe ............................................................... 9

SV-ADAHRS-200 module ................................................ 11

Altitude encoders ACK-30 / GAE 12 ................................ 14

Airspeed indicator ............................................................ 17

Altimeter .......................................................................... 17

Vertical speed indicator ................................................... 17

Flight hours counter ......................................................... 17

Stall warning transducer .................................................. 17

Drain sumps .................................................................... 18

Pitot-static system ........................................................... 20

34-20

ATTITUDE AND DIRECTION .......................................... 23

DESCRIPTION ........................................................................ 23

TROUBLESHOOTING ............................................................. 25

MAINTENANCE PRACTICES ................................................. 26

SV-D1000 display ............................................................ 26

Magnetic compass .......................................................... 26

Standby bank indicator .................................................... 26

Effectivity:

ALL

12. 06. 2020

NAVIGATION

34-40

INDEPENDENT POSITION DETERMINING ................... 27

DESCRIPTION ........................................................................ 27

MAINTENANCE PRACTICES ................................................. 28

FLARM, ADS-B Antenna ................................................ 28

TRX-1500 traffic sensor .................................................. 30

AT-1 traffic sensor .......................................................... 32

FLARM Antenna AV-75 .................................................. 34

VHF COMM antenna ...................................................... 36

34-50

DEPENDENT POSITION DETERMINING ....................... 37

DESCRIPTION ........................................................................ 37

MAINTENANCE PRACTICES ................................................. 39

Garmin GNC 255A NAV/COMM ..................................... 39

Garmin GTX 328 / GTX 335 transponder ....................... 39

VOR/LOC antenna .......................................................... 39

Transponder antenna...................................................... 39

SV-GPS-250 antenna ..................................................... 41

TRX / AT-1 GPS antenna ............................................... 43

GA 35 GPS antenna ....................................................... 44

GENERAL

NAVIGATION

34-00 GENERAL

INTRODUCTION

This  chapter  describes  the  navigation  systems,  units,  and  components  which
provide  aircraft  navigational  information.  Included  are  pitot-static,  compass,
navigation  systems,  and  indicators.  The  subjects  to  be  covered  in  this  chapter
are as follows:

The  Flight  Environmental  Data/Pitot  Static  section  describes  systems  which
sense  environmental  conditions  and  use  the  data  to  influence  navigation
of the aircraft. This includes components that depend on the pitot-static system
such  as  airspeed  indicator,  altimeter,  vertical  speed  indicator  and  ADAHRS
module of the Dynon SkyView system.

The Attitude and Direction section describes systems which use magnetic,
gyroscopic and inertia forces. This includes Dynon SkyView system and
the magnetic compass.

The Independent Position Determining section describes systems which provide
information to determine position from sources which are mainly independent
of ground installations. This includes the global positioning system and traffic
sensor.

The Dependent Position Determining  section describes systems which provide
information  to  determine  position  from  sources  which  are  mainly  dependent
on  ground  installations.  This  includes  systems  such  as  radio  navigational  aids
and transponder.

Wiring diagram of above mentioned equipment is described in the Aircraft Wiring
Manual (Doc. No. AS-AWM-01-000).

FLIGHT ENVIRONMENTAL DATA

Page 34-5

NAVIGATION

34-10 FLIGHT ENVIRONMENTAL DATA

1. DESCRIPTION

Arrangement and scheme of the pitot-static system is given on the Fig. 34-1.

The  Pitot-static  probe (1)  is  installed  under  the  right  wing.  It  receives  total  pressure
(hoses  marked  “P”),  static  pressure  (hoses  marked  “S”)  and  is  equipped  with  AOA
sensing (hoses marked “A”).
Pressure distribution to individual instruments on the airspeed indicator (3), altimeter
(4), vertical speed indicator (5) expansion bottle (8), flight hours counter (6), altitude
encoder  (7),  ADAHRS  module  (2)  and  stall  warning  transducer  (9)  (Chapter  31-50)
in the cockpit is performed through the flexible plastic hoses. There are also three drain
sumps (10) included in the pitot-static system.

NOTE

ADAHRS module is a part of the Dynon SkyView system, which is described
in Chapter 34-20.

Effectivity:

ALL

29. 01. 2020

NAVIGATION

– Pitot-static probe

– Flight hours counter

– ADAHRS module

– Altitude encoder

– Airspeed indicator

– Expansion bottle

– Altimeter

– Stall warning transducer

– Vertical speed indicator

– Drain sumps

Fig. 34-1 Pitot-Static System

FLIGHT ENVIRONMENTAL DATA

Page 34-7

NAVIGATION

TROUBLESHOOTING

TROUBLE

POSSIBLE CAUSE

REMEDY

Pitot static system

Low or sluggish airspeed
indication. Normal
altimeter and vertical
speed indication.

Pitot-static probe
deformed. Leak or
obstruction in total line.

Repair or replace
damaged component.

Incorrect or sluggish
response on all three
pitot-static instruments.

Leaks or obstruction in
static line.

Repair or replace line.
Remove obstruction.

Vertical speed indicator

Pointer does not set on
zero.

Leaking or ruptured
diaphragm.

Substitute known-good
indicator and check
reading. Replace or repair
instrument.

Pointer fails to respond.

Obstruction in static line.

Check line for obstruction.

Pointer oscillates or fails
to respond.

Leaks in static line.

Check line for obstruction.

Defective instrument.

Replace or repair
instrument.

Excessive vibration
caused by loose mounting
bolts.

Tighten mounting bolts.

Excessive tube vibration.

Tighten clamps and
connections.

Airspeed indicator

Pointer fails to respond or
indicates improperly.

Leak in instrument case.

Replace or repair
instrument.

Obstruction in total line.

Check line for obstruction.

Incorrect indication or
pointer oscillates.

Leak in total or static lines. Repair or replace

damaged lines. Tighten
connections.

Leaking or ruptured
diaphragm.

Substitute know-good
indicator and check
reading. Replace or repair
instrument.

Content .. 24 25 26 27 ..