WT9 Dynamic LSA. AIRCRAFT MAINTENANCE MANUAL (AS-AMM-01-000, 22. 05. 2017) - page 36

FLIGHT COMPARTMENT

WINDOWS

(1) Windshield removal:

(a) Remove canopy (Chapter 52-10).

(b) Remove vent windows (5.B.(1)).

of the windshield to gain access to the bonding flange. The windshield
should be cut as close as possible to the canopy frame. Use care
to prevent damage to the canopy frame.

CAUTION

EXERCISE

CARE

PREVENT

THE

REMOVAL

OF LAMINATE FROM THE CANOPY FRAME WHEN CUTTING
AND REMOVING THE ADHESIVE FROM GAP BETWEEN
THE CANOPY FRAME AND WINDSHIELD. IF LAMINATE IS
DAMAGED, IT MUST BE REPAIRED PRIOR TO INSTALLING
THE NEW WINDSHIELD.

(d) Cut remainders of the windshield in a perpendicular direction to around

10 cm strips (see Fig. 56-2).

(e) Cut adhesive from gap between canopy frame and windshield strips

using a small knife. While pushing on the windshield strips, follow
the edge of the canopy frame with the tip of the blade, then cut back
towards the canopy frame to remove adhesive (see Fig. 56-2).

(f)

Using a knife, isopropyl alcohol and sandpaper, remove all remaining
adhesive from the canopy frame bonding flange.

Effectivity:

ALL

24. 11. 2020

WINDOWS

Fig. 56-2 Windshield Removal

FLIGHT COMPARTMENT

WINDOWS

(2) Windshield installation:

CAUTION

EXERCISE CARE TO PROTECT THE INNER AND OUTER
WINDSHIELD

SURFACES

FROM

DAMAGE

DURING

THE INSTALLATION PROCESS.

(a) Inspect canopy frame bonding flange for any remaining adhesive

or contaminates, remove and clean if necessary.

(b) Cover the flight compartment and instrument panel with a foil

to prevent contamination.

(d) Attach the cover foil to the windshield in the distance of 30 mm

from the edge of the windshield.

(e) Remove peel ply from bonding flange of the canopy frame (only if new

canopy frame is installed).

(f)

Fit the windshield to the canopy frame and grind edges of the glass
so that between windshield and canopy frame remains equal gap
of 2.5 mm (see Fig. 56-3).

(g) Using the tape, fix the windshield on the canopy frame. Inspect

the windshield for proper fit. The windshield must have equal gap
of 2.5 mm around the perimeter of the windshield.

(h) Make several alignment marks around edges of masking tape

on the canopy frame and on masking tape on the windshield

(i)

Remove the windshield from the canopy frame and apply protective
tape on inner side of the windshield, which copies outer edge
of protective tape applied in previous step.

(j)

Using  sandpaper,  abrade  the  bonding  flange  of  the  windshield  and
canopy  frame.  Clean  bonding  surfaces  from  debris  and  dust.  Apply
a continuous piece of a foam tape around the inner edge of the canopy
frame.

(k) Mix the adhesive from 250 g of adhesive component A + 42 g

of adhesive component B. Thicken adhesive with cotton flakes (5 g)
and Aerosil (2 g) into the consistency of a paste and apply it
on the canopy bonding flange.

(l)

Carefully  place  the  windshield  to  the  canopy  frame  and  secure
the  windshield  into  position  making  sure  the  alignment  marks  made
earlier  (step  (h))  are  aligned  and  that  the  contour  of  the  windshield
matches the contour of the canopy frame.

(m) Remove adhesive excesses from the gap and let the adhesive

to harden.

(n) After curing, remove adhesive excesses from the gap. Fill the gap

with epoxy mixture thickened with brown microballoons.

(o) Install vent windows (5.B.(1)).

Effectivity:

ALL

24. 11. 2020

WINDOWS

Fig. 56-3 Windshield Installation

FLIGHT COMPARTMENT

WINDOWS

Vent windows

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

Allen key 2

1 pc

Persons

Tab. 56-2 Recommended tools, materials, persons and documentation

NOTE

Described is removal and installation of one of vent windows.

(1) Vent window removal:

(a) Remove bolts (7, Fig. 56-4) which connect upper rail (3) to windshield

(1); Remove stop plate (8) and upper rail (3).

(b) Remove slider (5) including springs (6). Be careful not to lose springs.

to slider (5), which can jump out of the rail.

(d) Remove lower slider (5) including springs (6).

(e) Unscrew bolts (7) from windshield side; Remove stop plate (8) and

lower rail (4).

(2) Vent window installation:

(a) If necessary, drill holes according to Fig. 56-4.

(b) Fix lower rail (4, Fig. 56-4) to windshield (1) using bolts (7).

Use foremost bolt to fix the stop plate (8). Do not tighten bolts yet.

along lower edge of vent window (2). Lug of vent window has to fit into
slider groove. Springs have to touch inner side of the vent window.

(d) Carefully pull down pre-assembled vent window (2) along with slider

(5) and springs (6) into lower rail (4). Pay attention to proper window
orientation.

(e) Repeat step (c) to fit slider (5) to upper edge of vent window (2).

(f)

Fix upper rail (3) to windshield (1) using bolts (7). Use foremost bolt
to fix the stop plate (8). Do not tighten bolts yet.

(g) Slide the vent window and check functionality.

(h) Finalize all bolts (7).

Effectivity:

ALL

24. 11. 2020

WINDOWS

– Windshield

– Slider

– Side window

– Spring

– Upper rail

– Bolt M3 x 6

– Lower rail

– Stop plate

Fig. 56-4 Vent Window Installation

FLIGHT COMPARTMENT

WINDOWS

Side windows

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. 56-3 Recommended tools, materials, persons and documentation

NOTE

Described is removal and installation of one of side windows.

Effectivity:

ALL

24. 11. 2020

WINDOWS

(1) Side window removal:

(a) Use a grinding tool and a cut-off disk to cut out the inner portion

of the side window to gain access to the bonding flange. The window
should be cut as close as possible to the fuselage flange. Use care
to prevent damage to the fuselage.

CAUTION

EXERCISE

CARE

PREVENT

THE

REMOVAL

OF  LAMINATE  FROM  THE  FUSELAGE  FLANGE  WHEN
CUTTING  AND  REMOVING  THE  ADHESIVE  FROM  GAP
BETWEEN  THE  FUSELAGE  FLANGE  AND  SIDE  WINDOW.
IF LAMINATE IS DAMAGED, IT MUST BE REPAIRED PRIOR
TO INSTALLING THE NEW SIDE WINDOW.

(b) Cut remainders of the side window in a perpendicular direction

to around 10 cm strips (see Fig. 56-5).

strips using a small knife. While pushing on the window strips, follow
the edge of the fuselage flange with the tip of the blade, then cut back
towards the fuselage flange to remove adhesive (see Fig. 56-5).

(d) Using a knife, isopropyl alcohol and sandpaper, remove all remaining

adhesive from the fuselage bonding flange.

FLIGHT COMPARTMENT

WINDOWS

Fig. 56-5 Side Window Removal

Effectivity:

ALL

24. 11. 2020

WINDOWS

(2) Side window installation:

CAUTION

EXERCISE CARE TO PROTECT THE INNER AND OUTER
SIDE OF THE SIDE WINDOW SURFACES FROM DAMAGE
DURING THE INSTALLATION PROCESS.

(a) Inspect fuselage bonding flange for any remaining adhesive

or contaminates, remove and clean if necessary.

(b) Cover the interior with a foil to prevent contamination.

from the edge of the window.

(d) Fit the window to the fuselage and grind edges of the glass so that

between window and fuselage remains equal gap of 2.5 mm
(see Fig. 56-6).

(e) Using the tape, fix the window on the fuselage. Inspect the window

for proper fit. The windshield must have equal gap of 2.5 mm around
the perimeter of the windshield.

(f)

Make several alignment marks around edges of masking tape
on the fuselage and on masking tape on the window

(g) Remove the window from the fuselage and apply protective tape

on inner side of the window, which copies outer edge of protective tape
applied in previous step.

(h) Using sandpaper, abrade the bonding flange of the side window and

fuselage. Clean bonding surfaces from debris and dust.
Apply a continuous piece of a foam tape around the inner edge
of the fuselage.

(i)

Mix the adhesive from 100 g of adhesive component A + 17 g
of adhesive component B. Thicken adhesive with cotton flakes (3 g)
and Aerosil (1 g) into the consistency of a paste and apply it
on the fuselage bonding flange.

(j)

Carefully place the side window to the canopy frame and secure
it on position making sure the alignment marks made earlier (step (f))
are aligned and that the contour of the window matches the contour
of the fuselage.

(k) Remove adhesive excesses from the gap.

(l)

After curing, remove adhesive excesses from the gap. Fill the gap
with epoxy mixture thickened with brown microballoons.

FLIGHT COMPARTMENT

WINDOWS

Fig. 56-6 Side Window Installation

CONTENTS

WINGS

57 WINGS

CONTENTS

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

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

57-20

OUTER WING ................................................................... 5

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

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

Wings ................................................................................ 5

57-40

LEADING EDGE DEVICES ............................................. 11

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

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

Stall strips ........................................................................ 11

57-50

WING FLAPS .................................................................. 15

DESCRIPTION ........................................................................ 15

MAINTENANCE PRACTICES ................................................. 15

Wing flaps ........................................................................ 15

57-60

AILERONS ...................................................................... 19

DESCRIPTION ........................................................................ 19

MAINTENANCE PRACTICES ................................................. 19

Ailerons ........................................................................... 19

Aileron trim tab actuator .................................................. 22

Aileron trim tab: ............................................................... 25

GENERAL

WINGS

GENERAL

1. INTRODUCTION

The WT9 Dynamic LSA is low-wing aircraft with cantilever wings. Each wing has
a flap inboard and aileron on the outboard trailing edge. The wings are glass/carbon
composite sandwich construction.
Refer to Chapter 27 for data on the control systems for the flaps and ailerons; refer
to Chapter 28 for data on the wing tanks. Refer to Chapter 51 for general repair data.

OUTER WING

WINGS

OUTER WING

1. DESCRIPTION

The  wing  has  trapezoidal  shape  and  is  glass/carbon  composite  sandwich
construction.  Upper  and  lower  skin  is  glued  together  with  one  main  spar  and  one
auxiliary  web.  Tie-down  point  is  attached  to  the  main  spar  of  each  wing.  Wing  tips
are fitted with winglets. There is a Pitot probe with angle of attack sensing installed
on the lower skin of the right wing.
The main spar of each wing is attached to the fuselage

’s main

spar through two main

pins. Auxiliary web of each wing is attached to the fuselage

’s auxiliary

spar through

an auxiliary pin. The outer pin is inserted through the access hole of the lower wing
surface. Inner pin is inserted from interior. Auxiliary pin is accessible from rear side,
after disconnecting the flap control and folding down the flap.
There is an integral fuel tank in each wing, with volume 26 l. The fuel tank is located
in wing root section in front of main spar. The tank has aluminum filler neck with
lockable cap. The tank is equipped with drain valve, located in its lowest point, near
wing root rib. Wing fuel tank is interconnected to fuselage fuel tank with hoses.

2. MAINTENANCE PRACTICES

A. Wings

The aircraft has the possibility to disassemble wings for transportation purposes
or to save space in the hangar.

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

Socket 7

1 pc

Wrench 9

1 pc

Wrench 10

1 pc

Wrench 16

1 pc

Pliers

1 pc

Screwdriver

1 pc

Loctite 243

Vaseline

Persons

Tab. 57-1 Recommended tools, materials, persons and documentation

Effectivity:

ALL

22. 05. 2017

WINGS

(1) Outer wing removal:

(a) Drain the fuel tanks (Chapter 12-10)
(b) Remove the adhesive sealing tape covering the gap between wing

and the wing central section.

Fig. 06-2) by unscrewing bolts with washers.

(d) Disconnect aileron push rod by removing safety pin (9, Fig. 57-2),

unscrew the nut (7), remove the bolt (6) and washer (8).

CAUTION

BEFORE DISCONNECTING FLAP PUSH ROD, PROTECT
THE UPPER SURFACE OF THE WHEEL FAIRING AS THE
FLAP WILL FALL DOWN.

(e) Disconnect the wing flap lever by unscrewing the nut (15)

and removing the washer (16).

(f)

Hold the wing flap; disconnect the wing flap push rod (13)
by removing the split pin (12) and pulling out the pin (11).

(g) Remove safety pins (5) securing wing pins. Pull out all wing's pins

in the following order: first outside main pin (1, Fig. 57-1) through
the installation hole, second auxiliary pin (3) and third inner main pin
(2) in the cockpit. During this procedure slightly move the wingtip up
and down to unload pins.

(h) Release hose clamps (Chapter 28-20) on the fuel hoses.
(i)

Pull out the wing so that there is approximately 100 mm distance
between the wing central section and the wing root, unplug all hoses
and wires.

(j)

Carefully remove the wing and put it on soft mats. Protect all fuel
tank sockets from contamination by foreign objects with an adhesive
tape. Stick the wires and hoses to the wing root rib using adhesive
tape.

(k) If necessary, remove Pitot probe (Chapter 34-10). Applicable for right

wing only.

OUTER WING

WINGS

(2) Outer wing installation:

(a) If necessary, install Pitot probe (Chapter 34-10), applicable for right

wing only.

(b) Thoroughly clean and lubricate all the wing fittings and pins

with vaseline before each assembly (Chapter 12-20).

there will be distance approx. 100 mm between wing root and wing
central section.

(d) Connect the Pitot probe hoses (right wing only) and conductive

connection wiring; avoid of pitot-static hoses twisting. Put hose
clamps on fuel hoses.

(e) Push the wing further inside, pull on the wing fuel tank hoses

on the central section tanks sockets and pull the wing flap lever
(14, Fig. 57-2) on the central section flap hinge (10).

(f)

Push the wing fully into the fuselage main spar. Insert the outside pin
(3), inside pin (2) (slightly shake the wing up and down to make pin
insertion easier). Secure both pins with the safety pins (5).

(g) Insert the auxiliary pin (4) and secure it with the safety pin (5).
(h) Tighten the fuel hoses clamps (Chapter 28-20).
(i)

Lock the central section flap hinge using washer (16) and nut (15).

(j)

Connect the flap rod (13) to the wing flap lever bearing using a pin
(11) and lock with the split pin (12); during this procedure, put the flap
control lever to the flaps fully extended position.

(k) Connect aileron pull-push rods (17, 18) with bolt (6), nut (7)

and washer (8); secure the connection with safety pin (9).

(l)

Check the securing of all connections.

(m) Cover the gap between wing and wing central section using

an adhesive tape.

(n) Carry out test and check:

•

That pins are secured.

•

That the castle nut is secured with safety pin.

•

If all bolt connections are tight.

•

Plays on main hinges.

•

That fuel and Pitot/static hoses are securely connected.

•

Free movement of wing flaps and ailerons.

•

Draining and vent holes.

•

That no foreign objects remained in aircraft.

Content .. 34 35 36 37 ..