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WT9 Dynamic LSA. AIRCRAFT MAINTENANCE MANUAL (AS-AMM-01-000, 22. 05. 2017) - page 16

EMERGENCY

EQUIPMENT/

FURNISHINGS

(3) ELT antenna removal:

(a) Set switch on the unit to

OFF

position.

(b) Remove the baggage bulkhead cover (13, Chapter 06-00, Fig. 06-4).

(d) Unscrew the nut (3), remove the washer (4) and the antenna (1).

(e) Install the protective cover on the antenna connector.

(4) ELT antenna installation:

(a) Perform ELT programming (as required) and check battery

expiration.

(b) Remove the protective cover from the antenna connector.

block (6) and its bottom in the bracket.

(d) Insert the washer (4), screw and tighten the nut (3) to torque from 2.8

to 3.4 Nm.

(e) Connect the connector (2) to the antenna (4).

(f)

Perform the measurement of SWR and check that coax cable is not
short circuited.

(g) Install the baggage bulkhead cover (Chapter 06-00).

(h) Carry out an operational test - refer to the Installation and Operation

Manual ELT KANNAD 406 AF-COMPACT, Doc. No. DOC08038F
(Revision 05 or later) / Initial Installation Manual KANNAD
AF INTEGRA, Doc. No DOC09081E (Revision 04 or later) and
Operation Manual KANNAD AF INTEGRA Doc. No DOC09078E
(Revision 04 or later).

(5) ELT battery replacement:

ELT KANNAD 406 AF COMPACT: The transmitter battery expiration date
is fixed at 6 years after manufacturing. If no activation of the ELT occurs
during the battery lifetime, it shall be replaced 6 years after date of
manufacture.

ELT KANNAD AF INTEGRA: The transmitter battery expiration date is fixed
at 7 years after manufacturing. If no activation of the ELT occurs during the
battery lifetime, it shall be replaced 7 years after date of manufacture.

Battery replacement is mandatory:

•

after more than 1 hour of real transmission (cumulated duration);

•

before or on the battery expiration date;

•

after activation in emergency;

•

after an accidental activation with unknown time duration;

Effectivity:

ALL

29. 01. 2020

EQUIPMENT/
FURNISHINGS

CAUTION

ONLY ORIGINAL AND APPROVED BATTERY PACK INCLUDED IN
BATTERY KIT BAT200 (P/N S1840510-01) SUPPLIED BY OROLIA
S.A.S. CAN BE INSTALLED [SAFT-FRIWO, LITHIUM MANGANESE
DIOXIDE, 2 x M20 (D-TYPE) CELLS].

NOTE

For battery replacement

– refer to the Installation and Operation

Manual  ELT  KANNAD  406  AF-COMPACT,  Doc.  No.  DOC08038F
(Revision  05  or  later)  /  Initial  Installation  Manual  KANNAD
AF  INTEGRA,  Doc.  No  DOC09081E  (Revision  04  or  later)  and
Operation  Manual  KANNAD  AF  INTEGRA  Doc.  No  DOC09078E
(Revision 04 or later).

– ELT unit

– Connectors

– Mounting bracket

– Central tunnel

– Self-stripping strap

Fig. 25-8 ELT Transmitter Removal / Installation

EMERGENCY

EQUIPMENT/

FURNISHINGS

– ELT antenna

For information:

– Connector

– Bracket

– Nut

– Foam block

– Serrated washer

Fig. 25-9 ELT Antenna Removal / Installation

CONTENTS

FLIGHT CONTROLS

27 FLIGHT CONTROLS

CONTENTS

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

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

MAINTENANCE PRACTICES ................................................... 3

General principles ............................................................. 3

ADJUSTMENT / TEST ............................................................... 4

Values for deflection adjustment .......................................... 4

INSPECTION / CHECK ............................................................. 5

Check of plays in flight controls ......................................... 5

27-10

AILERON AND ROLL TRIM ............................................. 7

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

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

Aileron control ................................................................... 9

Torsion tube with control sticks ....................................... 14

Roll trim system ............................................................... 18

27-20

RUDDER ......................................................................... 19

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

MAINTENANCE PRACTICES ................................................. 21

Control cables ................................................................. 22

Remote control of pedals................................................. 26

Foot control ..................................................................... 28

27-30

ELEVATOR AND PITCH TRIM ....................................... 33

DESCRIPTION ........................................................................ 33

MAINTENANCE PRACTICES ................................................. 35

Push rods and levers ....................................................... 35

Pitch trim system ............................................................. 41

Bob weight ....................................................................... 45

GENERAL

FLIGHT CONTROLS

27-00 GENERAL

1. INTRODUCTION

This chapter describes operation and the adjustment of the flight controls. It also
describes the assembly of the flight controls. Refer to the related chapter for the data
on a specified system.

The aircraft is equipped with dual control systems for elevator, ailerons and rudder.

2. MAINTENANCE PRACTICES

General principles

WARNING

FOR CONNECTING THE ROTARY-MOVABLE PARTS OF THE FLIGHT
CONTROLS, THE SELF-LOCKING NUTS ARE PROHIBITED TO BE
USED.

AT INSTALLATION USE ALWAYS NEW AND UNDAMAGED LOCKING
ELEMENTS (COTTER PINS, LOCK WASHERS, SELF-LOCKING NUTS,
etc.).

At removals / installations adhere to general principles which are applicable to
all flight controls:

All bearings, ground surfaces of bolts and other moving parts of the flight
controls have to be greased (Chapter 12-20).
Friction surfaces of the ball joint bearings and sliding bearings have to be
lubricated before installation (Chapter 12-20).

Threaded parts of adjustable bearing ends and forks of all control push-pull rods
have to be screwed-in so that they cover the check holes in control pull rods
ends. So the minimum length of bearing end or fork threaded parts screwing in
the control pull rods, i.e. min. 10 mm (0.39 in), is ensured.

The ball join bearings and the ball bearings must rotate freely without any
jamming or excessive resistance.

Bolted joints, serving for connection of two each other movable parts of the
aircraft flight controls, should be tightened carefully with the wrench or only with
hand. The bolted joint is tightened only to eliminate axial plays of the
connection.

Immediately after tightening of each bolted joint, secure it with the castellated
nut, the cotter pin or the locking pin and check the joint for movability and its
axial play.

After removal and installation of the flight control parts and prior to returning the
aircraft to operation, check always all the flight control parts, which were subject
of your handling, for proper safety.

Orientation of bolts, locking pins and cotter pins:
Mount the bolts into joints according to the rule - from above downwards or
from the front backwards (considering the flight direction). If this principle is
observed, spontaneous dropping out the bolt from the joint is so precluded in

Effectivity:

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22. 05. 2017

FLIGHT CONTROLS

case of unlocking, unscrewing and dropping out the nut during operation. Use
the same principle also when securing the nuts with locking pins or cotter pins.

After installing control elements, always check them for free motion without any
jamming and verify proper safety of all nuts and bolts.

Prior to installing new push-pull rods, adjust their lengths to correspond to their
nominal sizes.

In the whole operating range of the flight controls there must be kept the
specified play between the structure and those movable parts of the control, at
which their motion could be blocked.

3. ADJUSTMENT / TEST

Values for deflection adjustment

WARNING

NON-OBSERVANCE OF CONTROL SURFACES, WING FLAPS OR TRIM
TABS SPECIFIED DEFLECTIONS CAN NEGATIVELY INFLUENCE THE
FLIGHT CHARACTERISTICS OF THE AIRCRAFT.

The control systems have specified deflections that must be always kept in the
course of the aircraft operation. After replacing the control system parts, after
adjusting the cable tension and in other necessary cases, the deflections of
control surfaces and wing flaps must be checked and adjusted as required. The
procedures for adjusting the control surfaces and wing flaps are provided in the
appropriate sections, which describe the individual flight control systems. The
values for checks and adjusting of control surfaces and wing flaps deflections
are given in appropriate chapters.

GENERAL

FLIGHT CONTROLS

4. INSPECTION / CHECK

Check of plays in flight controls

At the aircraft operation the flight control and elements become worn-out under
the influence of loading, vibrations etc. This wear is shown by increase of plays.
When the maximum allowable operating play is reached, the worn-out parts
(bearings, bolts, pins, guides etc.) must be replaced.

SYSTEM

PROCEDURE TO FIND
A PLAY

PROCEDURE
TO REMEDY A
PLAY

MAX.

PRODUCT

PLAY

MAX.

OPERATION

PLAY

Ailerons
control
system

Fix ailerons in neutral
position. Move the control
stick to the left and right to
find possible plays. Move
the control stick to the end
stops. Move the ailerons
to find possible plays.

Check condition
of bearings and
replace if
necessary.

2 mm /

0.078 in

5 mm /

0.197 in

Elevator
control
system

Fix elevator in neutral
position. Move the control
stick forward and
backward to find possible
plays. Move the control
stick to the end stops.
Move the elevator to find
possible plays

Check condition
of bearings and
replace if
necessary.

2 mm /

0.078 in

5 mm /

0.197 in

Flaps
control
system

Extend the flaps and
move the flap trailing
edge in the root section
up and down to find
possible plays. Perform
for each position of flaps.

Check condition
of slots at the top
of central tunnel.
Check the
condition of
bearings and
replace if
necessary.

2 mm /

0.078 in

5 mm /

0.197 in

Ruder
control
system

Fix the nose wheel and
move the pedals.

Fix the pedals and move
with rudder left/right) and
forward/backward.

Check the rudder
hinges play.

Check the
conditions of
bearing eyes of
push-pull rods.
and tension of
control cables.

1 mm /

0.039 in

2 mm /

0.078 in

Tab. 27-1 Maximum Permissible Plays

AILERON AND ROLL TRIM

FLIGHT CONTROLS

27-10 AILERON AND ROLL TRIM

1. DESCRIPTION

Ailerons are controlled through the control sticks, attached to the control stick's
torsion tube (7, Fig. 27-1). Movement from control sticks is transferred to the ailerons
through the push-pull rod 1 (1), push-pull rod 2 (2), bellcrank (3) and push-pull
rod 3 (4).
Push-pull rods 1 are equipped with adjustable bearing eye at one and revolving fork
at the other. Push-pull rods 2 are equipped with adjustable bearing eyes on both
ends and are guided in two guide bearings (6) in the wing (in the root rib and support
rib). Bellcranks are fitted with bearings and fixed in the consoles that are attached to
the main wing spar. Bellcranks provide necessary differentiation of the ailerons
deflections. The deflections of the ailerons are differentiated 1:1.6.

Push-pull rods 3 are equipped with adjustable bearing eyes on both ends and are
connected to the lever (6) on the aileron root ribs.

Range of aileron control movement is limited by stops (8

) on the control stick’s torsion

tube (7).

Roll trim tab is located only on the right aileron. The tab is operated through actuator
installed in the aileron and controlled with rocker switch installed on the pedestal
panel. Actuator and tab are interconnected with push-pull rod.

Trim tab position is displayed on the EFIS.

The only left handle is equipped with a control stick shaker that is part of stall warning
system (Chapter 31-50).

Wiring diagram of aileron trim is described in the Aircraft Wiring Manual (Doc. No.
AS-AWM-01-000).

Effectivity:

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FLIGHT CONTROLS

– Push-pull rod 1

– Lever

– Push-pull rod 2

– Guide bearing

– Bellcrank

– Torsion tube

– Push-pull rod 3

– Stop

Fig. 27-1 Aileron Control System

AILERON AND ROLL TRIM

FLIGHT CONTROLS

2. MAINTENANCE PRACTICES

Aileron control

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

Special wrench 10 (see Fig. 27-2)

1 pc

Wrench 9

1 pc

Socket set 10

1 pc

Ruler 20 cm

1 pc

Protractor with deflecting pointer

1 pc

Vaseline

1 pc

Serrated locking washer

ø6.4

Persons

Tab. 27-2 Recommended tools, materials, persons and documentation

Fig. 27-2 Special Wrench

Aileron control removal:

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

wing’s bottom surface.

(b) Disconnect the push rod (3, Fig. 27-3) from the bellcrank (4), by

removing nut (13), washers (15; 5) and bolt (10).

nut (13), washers (15; 17) and bolt (11).

NOTE

Use special wrench (Fig. 27-2) for disconnecting push rod (3)
from aileron.

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

(e) Disconnect the push rod (2, Fig. 27-3) from the bellcrank (4), by

removing nut (13), washers (15; 5) and bolt (10); disconnect ground
wires (28, 29).

(f)

Disconnect the push rod (1) from the control stick (21), by removing
nut (13), washer (15), ground wire (30) and bolt (8).

(g) Remove the bellcrank (4) from bracket (26), by removing nut (13),

washer (17) and bolt (11).

Effectivity:

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04. 07. 2019

FLIGHT CONTROLS

Aileron control installation:

(a) Thoroughly clean and lubricate all the aileron movable points and

other movable parts with Vaseline before each assembling
(Chapter 12-20).

(b) Before assembling check push rods for cracks and condition of

rivets. Check parallel alignment of swivel bearings (19, Fig. 27-3); on
new push rods, release locking nuts (12) and use new washers (16).

using bolt (11), washer (17) and nut (13); check free movement.

(d) Connect push rod (3) to bellcrank (4), using bolt (10), washers (5; 15)

and nut (13).

(e) Connect ground wire (28) to ground wire (29).

(f)

Connect push rod (3) to aileron using bolt (11), washers (15; 17) and
nut (13); if using a new push rod (3):

•

Adjust length of push rod (3) so that the lower deflection of the

aileron at the tip is 65 mm; at this point the aileron bellcrank (4)
must be touching the spar web.

NOTE

Use special wrench (Fig. 27-2) to attach push rod (3) to aileron.

(g) Slide the push rod (2) through the hole in the wing root. Connect

push rod (2) to bellcrank (4) using bolt (10), washers (15; 5) and nut
(13).

(h) Slide the push rod (1) through centre wing root hole. Connect push

rod (1) to control stick using bolt (8), ground wire (30), washer (17)
and nut (13).

(i)

Attach the wing (Chapter 57-10); if using new push rod(s) (1; 2):

•

Align aileron trailing edge with wing trailing edge and fix them.

•

Set control sticks vertical.

•

Adjust lengths of push rods (1; 2) so it is possible to connect them

with bolt (9).

•

Loosen aileron, leave control stick fixed.

(j)

Connect push rod (1) with push rod (2) using bolt (9), washer (15),
nut (14) and safety pin (18); connect ground wire (32) to wire (27).

(k) Set control sticks vertical.

(l)

Adjust length of push rod (3), to align aileron upper trailing edge with
wing bottom trailing edge.

(m) Screw new push rods to distribute equal lengths of threads. Tighten

every lock nut (12). Check parallel alignment of swivel bearings (19).

(n) Install transparent cover (9, Chapter 06-00, Fig. 06-3) using silicone

glue and white adhesive tape.

AILERON AND ROLL TRIM

FLIGHT CONTROLS

(o) Carry out test and check:

•

That the castle nuts are secured with cotter pins.

•

If all bolt connections are tight.

•

That all lock nuts are tight.

•

Free movement of aileron control system.

•

Alignment of the trailing edge of aileron and wing.

•

Neutral position and max. deflections.

•

Equal division of the threads on the push rods.

•

That no foreign objects remained in the aircraft.

Adjustment / test - aileron deflections:

Both ailerons must be adjusted simultaneously. Described is adjusting
of one side.

CONTROL SURFACE DEFLECTIONS

Control surface

Down

Distance measurement point

from the point of rotation

Aileron

25 ±2°

15 ±2°

252 mm

106 ±4 mm

65 ±4 mm

Tab. 27-2 Aileron Deflections

(a) Remove laminated seats (Chapter 25-10).

(b) Put protractor on trailing edge of aileron root.

(d)

Set the protractor to 0°- starting value for measuring.

(e) Deflect aileron to the lower (possibly upper) extreme position and

read the deflection value.

(f)

Check deflection values in accordance with Tab. 27-2.

(g) If deflections are not within range listed in Tab. 27-2, screw stop bolts

(7, Fig. 27-3) at torsion tube of control stick to adjust correct
deflections.

(h) Carry out test and check:

•

Deflections of ailerons.

•

If all lock nuts are tight.

•

That no foreign objects remain in the aircraft.

Effectivity:

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04. 07. 2019

FLIGHT CONTROLS

Fig. 27-3 Aileron Control Removal / Installation (page 1 of 2)

AILERON AND ROLL TRIM

FLIGHT CONTROLS

– Push-rod 1

– Washer ø6.4 x 12 x 0.5

– Push-rod 2

– Safety-pin ø1.4 x 20

– Push-rod 3

– Swivel bearing

– Bellcrank

– Aileron root rib

– Washer ø6.4 x 10 x 1.6

– Control stick

– Washer ø6.4 x 10 x 0.5

– Fork

– Bolt M6x16

– Castle nut M6

– Bolt M6x22

– Washer ø4.3 x 9 x 0.8

– Bolt M6x25

– Cotter pin 1.6 x 25

– Bolt M6x28

– Bracket

– Bolt M6x36

– Ground wire

– Nut M6

– Ground wire

– Self-locking nut M6

– Ground wire

– Castle nut M6

– Ground wire

– Washer ø6.4 x 12 x 1.6

– Clamp

– Serrated locking washer ø6.4

– Ground wire

Fig. 27-3 Aileron Control Removal / Installation (page 2 of 2)

Effectivity:

ALL

04. 07. 2019

FLIGHT CONTROLS

Torsion tube with control sticks

Torsion tube with control sticks removal:

(a) Remove laminated seats (Chapter 25-10).

(b) Remove pedestal panel (Chapter 27-50, 2.B.(1)).

sticks (21) by removing nut (13), washer (17), ground wire (30) and
bolt (8).

(d) Disconnect elevator control push-pull rod 1 (1, Fig. 27-11) from

torsion tube (21), by removing nut (16), washer (12) and bolt (11)
(Chapter 27-30, 2.A.(1)).

(e) Disconnect bob weight push-pull (3, Fig. 27-15) from torsion tube

(11), by removing nut (5), washer (8) and bolt (9) (Chapter 27-30,
2.C.(1))

(f)

On control sticks, pull out and unsolder wires from left handle with
control stick shaker (4) (Chapter 31-50) and from PTT buttons (25)
(Chapter 23-50).

(g) Remove aft part of bushing (8, Fig. 27-4) from left and right side

of torsion tube (6), by unscrewing bolts (16) and removing washers
(21; 23) and ground wire (12) from right part of bushing.

(h) If necessary, remove front part of bushing (7) from left and right side

of main beam by unscrewing bolts (15) and removing washers (22;
23).

(i)

Pull and remove torsion tube (6) with control sticks through opening
in central tunnel.

NOTE

Control stick assembly is composed from items No. 2; 4; 13; 25
for left stick and No. 3; 5; 13; 25 for right stick. Left handle (4) is
equipped with a stick shaker.

(j)

Remove left handle with stick shaker (4) and right handle (5), by
unscrewing hexagon head bolt (13).

NOTE

It may be necessary to use bigger force.

(k) Disconnect connecting push rod (1) from a control sticks (2; 3), by

removing nuts (19), washers (20), ground wire (10) and bolts (9).

(l)

Disconnect left control stick (2) from torsion tube (6) by unscrewing
nut (19), washer (20) and bolt (17).

(m) Disconnect right control stick (3) from torsion tube (6) by unscrewing

nut (19), washer (21), ground wire (12) and bolt (17).

(n) If necessary, remove stop bolts by releasing nut (18) and unscrew

bolt (14).

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