WT9 Dynamic LSA. AIRCRAFT MAINTENANCE MANUAL (AS-AMM-01-000, 22. 05. 2017) - page 35

FUSELAGE STRUCTURE

FUSELAGE

53-10 FUSELAGE STRUCTURE

1. DESCRIPTION

Fuselage is monocoque glass/carbon composite construction consisting of three
parts that are bonded together: left side (1, Fig. 53-1), right side (2) and lower section
(3). There is shaped fuselage end and a rear lower fin bonded to the fuselage to
enlarge the area of stabilizing surface.

The fuselage sandwich shell is stiffened with firewall, bulkheads, ribs, stiffeners and
interior components creating cockpit. Major items of structure are main (4) and
auxiliary spar (5) to which the wings are attached. Main and auxiliary spar are
bonded in the central section of fuselage. The caps of these spars are made of
carbon rovings and the web is made of glass fabrics, foam panels with plywood
inserts.

There is a steel rope for emergency parachute system incorporated in the right side
of fuselage.

The plywood firewall (6) to which the engine is attached is stiffened with a carbon
stiffener, interior floor and rescue system board. Firewall has stiffened areas for
engine mount and nose landing gear leg attaching. From the engine compartment is
covered with a stainless steel shield.

In the cockpit there are two not adjustable seats which are arranged side by side.
The crew space is limited by firewall in the front and backrest (8) in the rear. In the
middle of cockpit there is a central tunnel which divides cockpit for left and right side
and passes through the baggage compartment which is also divided in two sections.
Baggage compartment is limited by backrest in the front and by baggage bulkhead
(9) in the rear. Baggage bulkhead is sloped in the upper section and fitted with
covered opening allowing access to the rear section of fuselage. Rear section of
fuselage is stiffened with the elliptical bulkheads. On the both sides of the fuselage
there are windows in the baggage compartment.

Vertical stabilizer (11) sandwich shell construction and is integral part of fuselage.
Rudder hinges are attached to the rear web of vertical stabilizer. The horizontal
stabilizer is fixed bonded to the fuselage and is sandwich shell construction with a
rear web (Chapter 55-10).

Integral fuel tanks are located in the forward box of wing central section (3) on the left
and right sides.

In the wing central section are bonded ribs to which the main landing gear legs are
attached.

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– Left side

– Firewall

– Right side

– Central tunnel

– Lower (wing central) section

– Backrest

– Main spar

– Baggage bulkhead

– Auxiliary spar

– Vertical stabilizer

Fig. 53-1 Fuselage Structure

FUSELAGE STRUCTURE

FUSELAGE

2. MAINTENANCE PRACTICES

Fuselage is made from composite materials, no servicing is required. Repairs of the
fuselage are described in Chapter 51.

CONTENTS

STABILIZERS

55 STABILIZERS

CONTENTS

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

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

55-10

HORIZONTAL STABILIZER ............................................. 5

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

MAINTENANCE PRACTICES ................................................... 5

Horizontal stabilizer ........................................................... 5

55-20

ELEVATOR ....................................................................... 7

DESCRIPTION .......................................................................... 7

MAINTENANCE PRACTICES ................................................... 7

Elevator ............................................................................. 7

55-30

VERTICAL STABILIZER ................................................... 9

DESCRIPTION .......................................................................... 9

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

Vertical stabilizer ............................................................... 9

55-40

RUDDER ......................................................................... 11

DESCRIPTION ........................................................................ 11

MAINTENANCE PRACTICES ................................................. 11

Rudder............................................................................. 11

GENERAL

STABILIZERS

55-00 GENERAL

1. INTRODUCTION

The aircraft has conventional tail configuration, with horizontal stabilizer located in
bottom part of fin. The empennage consists of vertical stabilizer with rudder and
horizontal stabilizer with elevator.

Vertical stabilizer is integral part of fuselage. The horizontal stabilizer is bonded into
the fuselage.

HORIZONTAL STABILIZER

STABILIZERS

55-10 HORIZONTAL STABILIZER

1. DESCRIPTION

Horizontal stabilizer is a glass/carbon composite sandwich construction. It consists of
upper and lower skin, auxiliary web and a web inside of stabilizer up to ¼ of stabilizer
span from the plane of symmetry.

2. MAINTENANCE PRACTICES

Horizontal stabilizer

Because the horizontal stabilizer is made from composite materials and is
bonded into the fuselage, no servicing is required.

ELEVATOR

STABILIZERS

55-20 ELEVATOR

1. DESCRIPTION

Elevator is a glass/carbon composite sandwich construction. It consists of upper and
lower skin and ribs.

Each half of the elevator is attached to the horizontal stabilizer through two carbon
hinges. Both halves of the elevator are connected together with elevator root hinge
located in the

aircraft’s plane of symmetry.

Each half of elevator is fitted with a balance weight located in horn.

2. MAINTENANCE PRACTICES

Elevator

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

Wrench 10

1 pc

Self-locking nut M6

2 pcs

Thin self-locking nut M6

1 pc

Vaseline

Persons

Tab. 55-1 Recommended tools, materials, persons and documentation

NOTE

Described is removal and installation of one half of the elevator.

(1) Elevator removal:

(a) Secure the aircraft.

(b) Remove the rudder (Chapter 55-40).

(Chapter 27-30).

(d) Disconnect the half of the elevator (1) from the root fitting (6) by

unscrewing nuts (4; 5) and removing washers (2; 3).

(e) Pull the half of the elevator (1) along the hinge line outboards.

(2) Elevator installation:

(a) Thoroughly clean and lubricate all elevator hinges before each

assembling (Chapter 12-20).

(b) Put the half of the elevator (1, Fig. 55-1) on hinges of the horizontal

stabilizer. Fit the root fitting (6) on bolts.

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(d) Align trailing edges of both elevator halves and tighten nuts (4; 5).

(e) Connect the push-pull rod to the root fitting (6) (Chapter 27-30).

(f)

Install the rudder (Chapter 55-40).

(g) Carry out test and check:



Screw and nuts connections are tight.



Free plays.



Free movement of elevator.



Elevator deflection limits.



Alignment of elevator trailing edges.



Unobstructed draining and vent holes.

– Half of elevator

– Self-locking nut M6

– Washer ø6 x 12 x 1.6

– Thin self-locking nut M6

– Washer ø6 x 12 x 0.5

– Root fitting

Fig. 55-1 Elevator Removal / Installation

VERTICAL STABILIZER

STABILIZERS

55-30 VERTICAL STABILIZER

1. DESCRIPTION

Vertical stabilizer is a sandwich shell construction and is integral part of the fuselage.
There is an auxiliary web to which the rudder hinges are glued and the tip rib.

2. MAINTENANCE PRACTICES

Vertical stabilizer

Because the vertical stabilizer is made from composite materials and is integral
part of fuselage, no servicing is required.

RUDDER

STABILIZERS

55-40 RUDDER

1. DESCRIPTION

The rudder is a glass/carbon composite sandwich construction. The rudder is
attached to the fin through two hinges and one root hinge.

Rudder is fitted with a balance weight located in its horn.

2. MAINTENANCE PRACTICES

Rudder

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

Wrench 10

2 pcs

Socket set 10

1 pc

Pliers

1 pc

Screwdriver

1 pc

Tensometer

1 pc

Vaseline

White adhesive tape 12 mm

Self-locking nut M6

2 pcs

Split pin ø1.6 x 16

1 pc

Blinder

ø25 mm

3 pcs

Persons

Tab. 55-2 Recommended tools, materials, persons and documentation

(1) Rudder removal:

(a) Secure the aircraft.

(b) Remove blinders (11, Fig. 55-2) - white stickers, located on both

sides of the fuselage (right below rudder root hinge) and in the
bottom part of the fuselage.

rear part, right below rudder root hinge.

(d) Unscrew castle nut (7) and remove washer (6) through the hole

located in the bottom rear part of the fuselage.

(e) Disconnect control cables (5) by unscrewing nuts (3), removing

washers (6), bolts (2) and distance tubes (4).

(f)

Lift the rudder (1) to remove it from hinges. Remove the washer (10)
from root hinge

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STABILIZERS

(2) Rudder installation:

(a) Thoroughly clean and lubricate all the rudder hinges and other

movable parts with Vaseline before each assembling
(Chapter 12-20). Do not lubricate the thread of the rudder root hinge.

(b) Put the washer (10, Fig. 55-2) on the rudder root hinge.

(d) Through the maintenance holes located in the side and in the bottom

of the fuselage rear part, put the washer (6), tighten castle nut (7)
and secure it with split pin (8).

(e) Stick new 25 mm blinders (11).

(f)

Connect rudder control cables (5) to the rudder control arms (9), by
using bolts (2), distance tubes (4), washers (6) and tighten new self-
locking nuts (3).

(g) Check the tension of rudder control cables with tensometer.

Allowable tension is 61-65 N, if not, adjust the tension according to
Chapter 27-20.

(h) Carry out test and check:



The castle nut is secured with a split pin.



All screw connections are tight.



Free movement of rudder (nose landing gear is unloaded).



Rudder deflection limits.



Tension of cables.



Unobstructed draining and vent holes.

RUDDER

STABILIZERS

– Rudder

– Castle nut M6

– Bolt M6 x 22

– Split pin ø1.6 x 16

– Self-locking nut M6

– Rudder control arm

– Distance tube

– Washer ø6.4 x 12 x 0.5

– Control cable

– Blinder ø25 mm

– Washer ø6.4 x 12 x 1.6

Fig. 55-2 Rudder Removal / Installation

GENERAL

WINDOWS

56-00 GENERAL

1. INTRODUCTION

The aircraft is equipped with a windshield and two side windows in (one on left and
one on right side).

The windshield and both side windows are made of stretched Plexiglas. The windshield
is bonded to the canopy frame, side windows are bonded to the fuselage structure.
Side windows are fixed and cannot be opened.

FLIGHT COMPARTMENT

WINDOWS

56-10 FLIGHT COMPARTMENT

1. DESCRIPTION

The aircraft has a one-piece tilting canopy, which is equipped with 3 mm thick Plexiglas
windshield (1, Fig. 56-1) and side windows (2) on both sides of fuselage.

– Windshield

– Side window (LH)

Fig. 56-1 Windows

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WINDOWS

2. MAINTENANCE PRACTICES

Windshield

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

Grinding tool

1 pc

Masking tape

Cover foil

Sandpaper 80 grit

Cleaner Isopropyl alcohol

Adhesive 1, component A - Swiftbond 9622 +
Adhesive 1, component B - Swifthardener 9533

Adhesive 2, component A - K

örapur 666/60 +

Adhesive 2, component B - K

öracur TH 650

Cotton flakes

Aerosil

Microbaloons

Drill

1 pc

Drill bit

ø4 mm

1 pc

Dremel rotary tool

1 pc

Engraving cutter

1 pc

Plastic scraper

1 pc

Foam tape 4 mm SSA Moll 10406

Application spatula

1 pc

Knife

1 pc

Cotton gloves (clean, lint free)

Two pairs

Cotton cloth (clean and lint free)

Persons

Tab. 56-1 Recommended tools, materials, persons and documentation

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