WT9 Dynamic LSA. AIRCRAFT MAINTENANCE MANUAL (AS-AMM-01-000, 22. 05. 2017) - page 37

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(3) Outer wing inspection / check:

In the following table are shown permissible plays for wing attachment.
These values should be not exceeded in operation:

SYSTEM

PROCEDURE TO
FIND A PLAY

PROCEDURE
TO REMEDY A
PLAY

MAX.

PRODUCT

PLAY

MAX.

OPERATION

PLAY

Wing

–

Wing

central section
attachment

Move the wing tip
up and down to find
possible plays.

Check the wing
pins. Replace if
necessary.

0 mm /

0.000 in

(at the wing

tip)

2 mm /

0.078 in

(at the wing

tip)

Tab. 57-2 Maximum Permissible Plays

Fig. 57-1 Order of Wing Pins Removal / Installation

OUTER WING

WINGS

Fig. 57-2 Wing Removal / Installation (page 1 of 2)

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–

Wing

–

Central section flap hinge

–

Inside main pin

–

6 x 21.5

–

Outside main pin

–

Split pin

1.6 x 25

–

Auxiliary pin

–

Push rod

–

Safety pin

–

Flap lever

–

Bolt M6 x 25

–

Self-locking nut M6

–

Castle nut M6

–

Washer

6.4 x 10 x 1.6

–

Washer

6.4 x 12 x 1.6

–

Push-rod 2

–

Safety-pin

1.3 x 23

–

Push-rod 1

Fig. 57-2 Wing Removal / Installation (page 2 of 2)

LEADING EDGE DEVICES

WINGS

LEADING EDGE DEVICES

1. DESCRIPTION

To improve stall behaviour of an aircraft, stall strips are installed on outer wing (LH and
RH, marked as 200 mm stall strip (2) on Fig. 57-3) and wing central section (LH and RH,
marked as 400 mm stall strip (1)).

2. MAINTENANCE PRACTICES

A. Stall strips

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

Knife

1 pc

Sand paper

Araldite (2-compound epoxy adhesive)

Persons

Tab. 57-3 Recommended tools, materials, persons and documentation

NOTE:

Described is removal and installation of one of stall strip.

(1) Stall strips removal:

(a) Using hot air, heat the stall strip up to app. 60

C. The resin, used to

glue the strip to leading edge will become softer.

CAUTION

DO NOT OVERHEAT THE AREA UNDER AND AROUND THE
STALL STRIP TO AVOID OF WING STRUCTURE DAMAGE.

(b) Using knife, carefully remove the stall strip.

(2) Stall strips installation:

(a) Mark position of stall strip on leading edge according dimensions on

Fig. 57-4.

(b)  Sand the leading edge area under the stall strip and degrease.
(c)  Mask surrounding area with masking tape.
(d)  Bond  stall  strip  to  leading  edge  using  araldite.  Remove  excessive

glue. Let it to harden.

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–

400 mm stall strip

–

200 mm stall strip

Fig. 57-3 Stall strip position

LEADING EDGE DEVICES

WINGS

–

400 mm stall strip

–

200 mm stall strip

Fig. 57-4 Stall strip position

WING FLAPS

WINGS

WING FLAPS

3. DESCRIPTION

Installed are slotted wing flaps that are glass/carbon composite sandwich
construction. Wing flap consists of upper and lower skin, ribs and a web. Each wing
flap is attached to the wing through three carbon hinges and one carbon/metal root
hinge.

4. MAINTENANCE PRACTICES

A. Wing flaps

Described is removal and installation of the left wing flap.

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

Wrench 9

1 pc

Pliers

1 pc

Screwdriver

1 pc

Serrated locking washer

6.4

3 pcs

Split pin

1.6 x 25

1 pc

Vaseline

Loctite 243

Persons

Tab. 57-4 Recommended tools, materials, persons and documentation

(1) Wing flap removal:

(a) If wing is disassembled, continue with point (f).
(b) If wing is assembled on aircraft, set the wing flaps lever to position 3

(flaps fully extended).

CAUTION

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

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(d) Remove the split pin (11) and pull out the pin (10). Disconnect

the push rod (13) from the wing flap lever (12).

(e) Retract wing flap and fix it with adhesive tape.
(f)

Remove split pins (11), unscrew nuts (8), remove washers (5; 6) and
pull out bolts (2) from three carbon hinges.

(g) Remove wing flap (1) from hinges.
(h) If necessary remove the wing flap lever (12), by unscrewing bolts (3)

and removing washers (4; 5).

(2) Wing flap installation:

(a) Thoroughly clean and lubricate all hinges, pins and bearings with

vaseline before each assembling (Chapter 12-20).

(b) If necessary install the wing flap lever (12, Fig. 57-5), using bolts (3)

and washers (4; 5).

(c)  Put the flap (1) in position on the aircraft; hold the flap.
(d)  Secure flap (with adhesive tape) to prevent falling.
(e)  Connect  flaps hinges to wing hinges using bolts (2), washers  (5;  6)

and nuts (8); secure joints with new split pins (11).

NOTE

Assembled wing flaps have to move easily. Wing flap will move
to lower position under its own weight when wing flap lever (12)
is not connected to push rod (13). If it does not, lubricate carbon
hinges or adjust tightness of nuts (8).

(f)

Check flap move to lower position due to its own weight.

(g) Connect push rod (13) to the wing flap lever (12) using pin (10);

secure joint with the new split pin (11).

(h) Carry out test and check:

•

That castle nuts are secured with split pins.

•

If all bolt connections are tight.

•

Free plays.

•

Free movement of flaps.

•

Draining and vent holes.

•

Alignment of the trailing edges of ailerons and wing.

•

Neutral position and deflections in all flap positions.

WING FLAPS

WINGS

–

Wing flap

–

Castle nut M6

–

Bolt M6 x 22

–

Self-locking nut M6

–

Bolt M6 x 35

–

6 x 21.5

–

Serrated locking washer

6.4

–

Split pin

1.6 x 25

–

Washer

6.4 x 12 x 0.5

–

Flap lever

–

Washer

6.4 x 12 x 1.6

–

Push rod

–

Washer

6.4 x 10 x 1.6

Fig. 57-5 Wing Flap Removal / Installation

AILERONS

WINGS

AILERONS

1. DESCRIPTION

Ailerons are glass/carbon composite sandwich construction. Aileron consists of upper
and lower skin, ribs and web. Each aileron is

attached to the wing’s upper skin

through three carbon hinges. The aileron is fitted with a balance weight.
The right aileron is equipped with an electrically actuated trim tab.
Wiring diagram of aileron trim is described in the Aircraft Wiring Manual
(Doc. No. AS-AWM-01-000).

2. MAINTENANCE PRACTICES

A. Ailerons

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

Wrench 9

1 pc

Punch ø2

1 pc

Punch ø5

1 pc

Hammer 100 g

1 pc

Socket 10

1 pc

Pliers

1 pc

Screwdriver

1 pc

Knife

1 pc

Split pin

1 pc

Roll pin

2 pcs

Covering label

1 pc

Double side tape 12 mm

White adhesive tape 12 mm

Adhesive tape

Vaseline

Persons

Tab. 57-5 Recommended tools, materials, persons and documentation

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WINGS

(1) Aileron removal:

(a) Remove transparent cover (9, Chapter 06-00 Fig. 06-3)

in wing’s

lower skin and disconnect push rod (10, Fig. 57-6) from bellcrank
(Chapter 27-10).

(b) Remove the Mylar tape (9), together with white tape (12) and double

sided tape (11).

(c) Secure aileron (with adhesive tape) to prevent of its falling.
(d) Remove split pin (8), unscrew nut (7), remove washers (4; 5) and bolt

(2) from aileron root hinge.

(e) Push out roll pins (6) using punch

tool ø2 mm and push out pins (3)

using punch tool ø5 mm from middle and tip hinge.

(f)

Carefully remove aileron with push rod from the wing and hold it.

(g) In case of the right aileron removal, disconnect electrical connector

from the trim tab servo box.

(h) Disconnect push rod (10) from aileron (1) (Chapter 27-10).
(i)

If necessary, remove PTFE tape (13) from aileron’s upper and lower

skin.

(2) Aileron installation:

(a) Thoroughly clean and lubricate all hinges, pins and bearings

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

(b) Connect push rod (10, Fig. 57-6) to the aileron (1) (Chapter 27-10).
(c) For right aileron installation, connect electrical connector to the trim

tab servo box.

(d) Put the aileron (1) in position on the aircraft; hold the aileron.
(e) Secure aileron (with adhesive tape) to prevent falling.
(f)

Insert pins (3) to the middle and tip hinges; secure them with the new
roll pins (6).

(g) Connect the aileron root hinge to wing hinge using bolt (2), washers

(4; 5) and nut (7); secure joint with the new split pin (8).

NOTE

The assembled aileron has to move easily. The aileron will
move to lower position due to its own weight when push rod

(10) isn´t connected to bellcrank. If it does not, apply more

lubricant to hinges or adjust tightness of the nut (7).

(h) Check if aileron moves to lower position under its own weight.
(i)

Connect push rod (10) to the bellcrank (Chapter 27-10).

(j)

Check adjustment of aileron control (Chapter 27-10).

(k)

If necessary, stick PTFE tape (13) on aileron’s upper and lower skin.

(l)

Remove old adhesive tapes and old glue from gap between wing and
aileron. Stick double side tape (11) on wing surface, install Mylar
tape (9) and then stick the white adhesive tape (12) on wing surface
and Mylar tape.

AILERONS

WINGS

(m) Carry out test and check:

•

That castle nuts are secured with split pins.

•

If all bolt connections are tight.

•

Free plays.

•

Free movement of ailerons.

•

Fitting of roll pins.

•

Draining and vent holes.

•

Alignment of the trailing edges of ailerons and wing.

•

Neutral position and deflection limits.

Fig. 57-4 Aileron Removal / Installation (page 1 of 2)

–

Aileron

–

Split pin ø1.6 x

–

Bolt M6 x 37

–

Mylar tape

–

Pin ø6 x 30

–

Push rod

–

Washer ø6.4 x 12 x 1.6

–

Double sided tape

–

Washer ø6.4 x 12 x 0.5

–

White tape

–

Roll pin ø2 x

–

PTFE tape

–

Castle nut M6

Fig. 57-6 Aileron Removal / Installation (page 2 of 2)

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B. Aileron trim tab actuator

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

Philips screwdriver

1 pc

Wrench 10

2 pcs

Pliers

1 pc

Socket 5.5

1 pc

Cotter pin

1 pc

Protractor with deflecting pointer

1 pc

Persons

Tab. 27-6 Recommended tools, materials, persons and documentation

(1) Aileron trim tab actuator removal:

(a) Open the

ROLL

circuit-breaker.

(b) Remove the right aileron (see 2.A.(1)).
(c) Unscrew nuts (7, Fig. 57-7), remove washers (8), bolts (9) and cover

(10).

(d) Remove the cotter pin (6), washer (5), pin (4) and disconnect the rod

(3) from the trim tab lever (12).

(e) Disconnect the electrical connector (2) from the connector (13).
(f)

Unscrew nuts (7), remove washers (8) and carefully remove
the actuator (1) from the box.

(g) As necessary, remove the cotter pin (6), washer (5), pin (4)

and disconnect the rod (3) from the actuator (1).

(2) Aileron trim tab actuator installation:

(a) If necessary, fit the rod (3, Fig. 57-7) to the actuator, insert pin (4)

into the hole, insert the washer (5) and secure with the new cotter pin
(6).

(b) Insert the trim tab actuator (1) into the box and fit it in place.
(c) Put nuts (7) with washers (8) on the bolts in the box and carefully

tighten nuts (7).

(d) Fit the rod (3) to the control lever (12), insert pin (4) into the hole,

insert the washer (5) and secure it with the new cotter pin (6).

(e) Connect the electrical connector (2) to the connector (13).

AILERONS

WINGS

(f)

Fit the cover (10) to the box, insert bolts (9) from top side, washers
(8) and nuts (7) from bottom side. Tighten nuts.

(g) Install the right aileron (see 2.A.(2))
(h) Close the ROLL circuit-breaker.
(i)

Carry out test and check:

•

If all bolt connections are tight.

•

That all lock nuts are tight.

•

Free movement of aileron control system.

•

Alignment of the trailing edges of ailerons and wing.

•

Neutral position and max. deflections.

•

Equal division of the threads on the push rods.

•

That no foreign objects remained in the aircraft.

(3) Adjustment / test

–

aileron trim tab deflections:

CONTROL SURFACE DEFLECTIONS

Control surface

Down

Distance measurement point

from the point of rotation

Trim tab

18 ±1°

20 ±1°

Tab. 27-7 Trim Tab Deflections

(a)  Set the aileron to neutral position.
(b)  Put protractor on trailing edge of aileron trim tab root.
(c)  Set the aileron trim tab to neutral position.
(d)

Set the protractor to 0°

- starting value for measuring.

(e) Deflect trim tab to the max. up and max. down possible position

and read the deflection value.

(f)

Check deflection values in accordance with Tab. 27-7.

(g) If deflections are not within range listed in Tab. 27-7, adjust forks

on the push pull rod (3, Fig. 57-7).

(h) Carry out test and check:

•

Deflections of aileron trim tab.

•

Rod ends are in safety.

•

That no foreign objects remain in the aircraft.

Effectivity:

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04. 07. 2019

WINGS

–

Actuator

–

Washer 3.2 x 7 x 0.5

–

Electrical connector

–

Bolt M3 x 12

–

Push-pull rod

–

Cover

–

Right aileron

–

Washer

–

Trim tab lever

–

Cotter pin

–

Electrical connector

–

Nut M3

Fig. 57-7 Aileron Trim Actuator Removal / Installation

AILERONS

WINGS

C. Aileron trim tab:

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

Hammer 100 g

1 pc

Pliers

1 pc

Locking wire ø 0

.8 mm

Vaseline

Persons

Tab. 57-8 Recommended tools, materials, persons and documentation

(1) Aileron trim tab removal:

(a)  Remove the right aileron (see 2.A.(1)).
(b)  Disconnect servo and push rod from the trim tab lever (3, Fig. 57-7).
(c)  Cut the locking wire which is securing hinge rod (2, Fig. 57-8).
(d)  Hold the trim tab and remove the hinge rod (2).
(e)  Remove the trim tab (1).

(2) Aileron trim tab installation

(a) Thoroughly clean and inspect hinges, lubricate the hinge rod

with vaseline (Chapter 12-20).

(b)  Align trim tab hinges with hinges on the aileron.
(c)  Carefully insert the hinge rod (2, Fig. 57-8).
(d)  Secure  end  of  the  rod  (2)  to  the  bracket  (4)  with  locking  wire  (3)

(Chapter 20-20).

(e) Connect servo push rod to the trim tab lever (3, Fig. 57-7).
(f)

Install the right aileron (see 2.A.(2)).

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