WT9 Dynamic LSA. AIRCRAFT MAINTENANCE MANUAL (AS-AMM-01-000, 22. 05. 2017) - page 34

Effectivity:

ALL

22. 05. 2017

STANDAR PRACTICES
AND STRUCTURES-
GENERAL

Fig. 51-5 Ply Lay-up (page 2 of 2)

Each fabric must be properly oriented with respect to the long side of the aircraft. The
patch must be composed of an equal number of layers as a repair area plus one
technology layer that prevents damage of the top layer due to finishing.

The table shows the layers necessary for repairs in order from the outer to the inner.

Repair the damage are allowed only 5 cm from the spar, rib or bulkhead. If there was
also damage the spar, bulkhead, contact the manufacturer.

If the collar on the leading edges of the wings and horizontal stabilizer is damaged, it
is necessary to laminate new ones.

REPAIRS

STANDARD PRACTICES

AND STRUCTURES-

GENERAL

ITEM

LAYER

POSITION

LAYER

WEAVE

DIRECTION

NOTE

Outer

02037

Technological

layer

Outer

02037

Outer

CF80

Outer

CF140

Herex

3 mm

Inner

CF80

Outer

92110

Technological

layer

Outer

92110

Herex

6 mm

Inner

92110

Outer

92110

Technological

layer

Outer

92110

Herex

3 mm

Inner

91111

92110

Technological

layer

92110

Only for the

leading edge

collar

92110

Only for the

leading edge

collar

91111

Outer

92110

Technological

layer

Outer

92110

Outer

92110

Herex

6 mm

Inner

91111

Outer

92110

Technological

layer

Outer

92110

Outer

CF200

Herex

8 mm

Inner

92110

Outer

92110

Technological

layer

Outer

92110

Outer

CF200

Outer

CF200

Herex

8 mm

Inner

92110

ITEM

LAYER

POSITION

LAYER

WEAVE

DIRECTION

NOTE

Outer

CF80

Technological

layer

Outer

CF80

Herex

5 mm

Inner

90070

Outer

CF80

Technological

layer

Outer

CF80

Outer

CF140

Herex

5 mm

Inner

90070

92110

Technological

layer

92110

90070

3x92110

Splicing collar

Outer

CF80

Technological

layer

Outer

CF80

Herex

3 mm

Inner

02037

Outer

92110

Technological

layer

Outer

92110

Outer

92110

Herex

5 a 8 mm

Inner

91111

Inner

92125

Outer

92110

Technological

layer

Outer

92110

Outer

92110

Herex

5 a 8 mm

Inner

91111

Technological

layer

91111

92125

Only 70 mm

around the

cutout of the

wheel and its

attachment

92125

Effectivity:

ALL

22. 05. 2017

STANDAR PRACTICES
AND STRUCTURES-
GENERAL

ITEM

LAYER

POSITION

LAYER

WEAVE

DIRECTION

NOTE

92110

Technological

layer

92110

Technological

layer

92110

CF200

91111

92110

Technological

layer

92110

CF200

18*

91111

Technological

layer

91111

CF200

CF140

19*

91111

Technological

layer

91111

CF200

CF140

Outer

92110

Technological

layer

Outer

92110

Outer

CF140

Herex

5 mm

Inner

91111

92110

Technological

layer

92110

91111

CF140

CF200

91111

ITEM

LAYER

POSITION

LAYER

WEAVE

DIRECTION

NOTE

Outer

92110

Technological

layer

Outer

92110

Outer

91111

Outer

CF140

Herex

5 mm

Inner

91111

92110

Technological

layer

92110

91111

Outer

92110

Technological

layer

Outer

92110

Herex

5 mm

Inner

91111

Outer

92110

Technological

layer

Outer

92110

Outer

92110

Herex

3 mm

Inner

02037

Outer

92110

Technological

layer

Outer

92110

Herex

3 mm

Inner

02037

92110

Technological

layer

92110

92125

* valid for the outer and as well as inner
shell

Tab. 51-3 Ply Lay-up

REPAIRS

STANDARD PRACTICES

AND STRUCTURES-

GENERAL

7. REPAIRS OF METAL PARTS

In case of a damage of any fittings, if a damage reason was not designate
immediately, contact the aircraft manufacturer. It is necessary take account to an
element function, a material composition, a processing technology and etc. The
aircraft manufacturer can evaluate all these factors only.

Welding should be carried out only by an approved aircraft welder. All welds made by
the aircraft manufacturer are by the Argon-arc welding method.

8. REPAIRS OF PLEXIGLASS

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

Driller

1.5

– 2.0

Persons

Tab. 51-4 Recommended tools, materials, persons and documentation

Most common damage which occurs on plexiglass are cracks, which usually start
around vent windows rails as result of using of these windows to open or close the
canopy.

When  the  crack  occurs,  it  is  important  to  stop  its  propagation  immediately  after
discovering  it.  This  can  be  done  by  drilling  a  hole  in  direction  of  crack  trajectory.
The  hole  has  to  be  drilled  perpendicular  to  surface,  on  farthermost  visible  point
of  the crack (crack tip).  This has to be done for each  crack tip, except  the end is in
hole, or on edge. Diameter of the hole should not be less than 1 mm, and not greater
than 2 mm.

9. TEST FLIGHT AFTER REPAIR

WARNING

ONLY QUALIFIED PILOT MAY PERFORM A TEST FLIGHT!

The test flight should be performed above all in following cases:

After repair or replace of fixed surfaces

– wing, fin, stabilizer, or control surfaces –

elevator, aileron and wing flap. Flight characteristics and aircraft stability can be
affected when above mentioned part is replaced or adjusted. Therefore a test flight
should be performed to check aircraft flight characteristics, control surfaces setting,
manoeuvrability, stability, and stall characteristics. The characteristics are check
during taxiing, takeoff, climbing, cruise, descent, approach and landing. The extend
of flight test necessary to perform depends on the extend of repair.

Effectivity:

ALL

04. 07. 2019

STANDAR PRACTICES
AND STRUCTURES-
GENERAL

Test flight flying time:

Test flight flying time depends on the extend of the tests necessary to perform
after a repair.

Aircraft inspection before a Test flight:

Prior to the test flight the aircraft shall be thoroughly inspected, weighed, found
faults debugged and the aircraft shall be prepared for the flight (replenishing
etc.).

Test crew:

Only qualified persons (test pilots) are permitted to perform a test flight. In-flight
found faults should be debugged forthwith the test flight

EXTERIOR FINISH REPAIR

STANDARD PRACTICES

AND STRUCTURES-

GENERAL

51-20 EXTERIOR FINISH REPAIR

1. REPAIR SURFACES

During the operational life of the aircraft, small scratches and dents may appear on
the composite surfaces. This damage needs to be repaired. Refinishing of the
damage is permitted as long as there is no damage to the fiber fabrics.

When control surfaces are painted, they must comply with weight and static moment
range according to Tab. 51-2.

Puttying

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

Sandpapers to density 240

Polyester putty

Benzine

Persons

Tab. 51-5 Recommended tools, materials, persons and documentation

(1) Instructions:

(a) Localize and mark every dent.

(b) Sand the paint on the dent and the surrounding area using

sandpaper 240.

(d) Mix required amount of putty, refer their manual.

(e) Apply required amount of putty on dent.

(f)

Let putty harden.

(g) Sand the repaired area with sandpaper 240.

(h) Any imperfections putty again and then re-sand.

(i)

Visually inspect and touch check. If surface is smooth without dents
continue with painting.

Effectivity:

ALL

22. 05. 2017

STANDAR PRACTICES
AND STRUCTURES-
GENERAL

Painting

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

Airbrush

1 pc

Brush

1 pc

Polishing pad

Sandpapers 400-2000

Mipa 4+1 2K HS -Filler

MIPA OC MISCHLACK-KONZENTRAT-Paint

MIPA 2K-

HÄRTER H5- Hardener

Mipa 2K- Thinner

Mipa C85 2K-HS-Clearcoat

Grinding paste

Polish

Benzine

Persons

Tab. 51-6 Recommended tools, materials, persons and documentation

(1) Instructions:

(a) Localize and mark every dent.

(b) Sand surface with sandpapers to 400.

(d) Mix required amount of Filler, refer their manual.

(e) Apply required amount of layers of Filler on surface to smooth

indentations.

(f)

Let filler harden.

(g) Smooth indentations with sandpapers to 1200.

(h) Any imperfections fill again and then smooth.

(i)

For small repairs use a brush, for bigger repairs use an airbrush.
Apply paint in thin layers. Allow to harden.

(j)

Polish surface with a grinding paste.

(k) Visually inspect and touch check that surface is smooth without

dents.

(l)

After painting on control surfaces their weight and inertia moment
must be checked.

GENERAL

DOORS

52-00 GENERAL

1. INTRODUCTION

The aircraft is equipped with the canopy which enables the access into the cockpit.

CANOPY FRAME

DOORS

52-10 CANOPY FRAME

1. DESCRIPTION

The  aircraft  has  a  one-piece  tilting  canopy  (Fig.  52-1).  Canopy  frame  is  attached
in front section to the fuselage using two hinges (2) and supported by two gas springs.
It is opened in upside-forward direction. Guide pins located on both sides of the canopy
frame ensures centering of the canopy during the closing. Canopy is equipped with 3
mm  thick  Plexiglas  windshield  and  sliding  windows  on  both  sides.  The  frame  (1)
is  a  hollow  laminate  structure,  through  which  flows  venting  air.  Canopy  is  fitted
with  eyeball  vents  on  both  sides  and  holes  for  blowing  of  windshield  (see
Chapter 21-20). Closing mechanism of canopy frame (3; 4) with handle (6) is situated
in the middle of the frame in rear part of the canopy frame and is accessible from both
- pilot and co-pilot seats. The canopy frame is also equipped with a canopy lock (5).
Closing  mechanism  is  secured  only  when  the  lock  lever  is  fully  plugged  backwards
(red ring indicates correct locking).

The towing version and aircraft from S/N 21001 are equipped with rear mirror fitting (7)
installed inside of canopy frame (1).

Fig. 52-1 Canopy Frame (page 1 of 2)

Effectivity:

ALL

24. 11. 2020

DOORS

– Canopy frame

– Canopy lock

– Canopy hinge

– Handle

– Canopy closing mechanism handle (exterior) 7 – Mirror fitting

– Canopy closing mechanism handle (interior)

Fig. 52-1 Canopy Frame (page 2 of 2)

CANOPY FRAME

DOORS

2. MAINTENANCE PRACTICES

Canopy frame

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

1 pc

Pliers

1 pc

Wrench 10

1 pc

Blinder

ø30 mm

2 pcs

Persons

Tab. 52-1 Recommended tools, materials, persons and documentation

(1) Canopy frame removal:

CAUTION

DURING CANOPY FRAME REMOVAL, PAY ATTENTION NOT
TO SCRATCH THE WINDSHIELD!

(a) Remove blinders (10, Fig. 52-2).

(b) Open the canopy frame (1).

frame (1) (see par. 2. B (1)).

(d) Remove safety pins (6), unscrew nuts (4) and remove washers (5).

(e) Remove the canopy frame hinge bolts (3).

(f)

Carefully remove the canopy frame (1).

(2) Canopy frame installation:

CAUTION

DURING CANOPY FRAME INSTALLATION, PAY ATTENTION NOT
TO SCRATCH THE WINDSHIELD!

(a) Place the canopy frame (1, Fig. 52-2) on the fuselage.

(b) Insert bolts (3) into hinges.

(d) Install washers (5), screws and tighten nuts (4); install safety pins (6)

(e) Connect upper end of gas springs (2) on both sides of the canopy

frame (1) (see par. 2. B (2)).

(f)

Stick new blinders (10).

Effectivity:

ALL

24. 11. 2020

DOORS

– Canopy

– Ball socket

– Gas spring

– Safety clip

– Bolt M6 x 47

– Ball stud

– Castle nut M6

– Blinder ø30 mm

– Washer 6.4 x 16 x 1.6

– Blinder ø25 mm (if rear mirror not installed)

– Safety pin 1.4 x 20

Fig. 52-2 Canopy Frame Removal / Installation

CANOPY FRAME

DOORS

Gas spring

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

1 pc

Pliers

1 pc

Persons

Tab. 52-1 Recommended tools, materials, persons and documentation

(1) Gas spring removal:

(a) Open the canopy frame (1, Fig. 52-2) and support it.

(b) Remove safety clips (8) from both ball sockets (7) of the gas spring.

(2) Gas spring installation:

(a) Inspect the gas spring (2, Fig. 52-2) whether it is not damaged.

(b) Insert ball socket (7) on the ball stud (9) in the canopy frame and

bottom ball socket (7) on the ball stud (9) in the fuselage.

Pay attention to proper gas spring orientation - cylinder part of the gas
spring has to be connected to the canopy frame (1), piston part has
to be connected to the fuselage.

CONTENTS

FUSELAGE

53 FUSELAGE

CONTENTS

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

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

53-10

FUSELAGE STRUCTURE ................................................ 5

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

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

GENERAL

FUSELAGE

53-00 GENERAL

1. INTRODUCTION

The fuselage is a monocoque structure made primarily of glass and carbon fibre
composite materials.

Chapter 53-10 gives the data for the fuselage structure.

Content .. 32 33 34 35 ..