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

RUDDER

FLIGHT CONTROLS

– Torsion tube R

11 - Allen bolt M6 x 20

– Torsion tube L

12 - Allen bolt M6 x 10

– Outer console

13 - Self-locking nut M6

– Inner console

14 - Cotter pin 1.6 x 25

– Bronze bushing

15 - Washer

ø6.4 x 12 x 1.6

– Pedal LL

16 - Washer

ø8.4 x 16 x 1.6

– Pedal RR

17 - Left lever spring

8 -

Pedal LR

18 - Right lever spring

9 -

Pedal RL

19 - Spring

10 - Pin

ø8 x 36

20 - Bayonet

Fig. 27-9 Foot Control Removal / Installation (page 2 of 2)

ELEVATOR AND PITCH TRIM

FLIGHT CONTROLS

27-30 ELEVATOR AND PITCH TRIM

1. DESCRIPTION

Both control sticks (1, Fig. 27-10) are fitted with bearings, attached to the control
stick's torsion tube (2) and linked inside of torsion tube with connecting push-pull rod
(3). Torsion tube turns in ball bearings (4) which are attached to the central section
main spar.

Elevator is controlled through 3 push-pull rods that are equipped with adjustable
bearing eyes. Push-pull rods are located in the central tunnel. Movement from control
sticks is transferred to the elevator through the push-pull rod 1 (5), two-armed lever
(6), push-pull rod 2 (7), support lever (8) and push-pull rod 3 (9) to the elevator lever
(10). Elevator lever is fixed to the both halves of elevator and hinged through the
bearing to the elevator root hinge (11). Elevator root hinge is attached to the
horizontal stabilizer aft web.

Range of elevator control movement is limited by the front stop (13) installed on the
central section main spar and the aft stop (12) (tube with a bolt installed inside of the
central tunnel).

There is a bob weight (14) installed at lever (15) and connected to the control stick's
torsion tube by push-pull rod (16).

Pitch trim system is connected to the push-pull rod 1 (5). Pitch trim consists of two
tension springs (18; 19). The springs are attached to the push-pull rod 1 (5) by
means of sleeves (19) and support lever (20). Support lever is operated through
actuator (21) and controlled by a rocker switch installed on the pedestal panel.

Position of the elevator trim is displayed on the EFIS.

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

Effectivity:

ALL

04. 07. 2019

FLIGHT CONTROLS

– Control stick

12 - Aft stop

– Torsion tube

13 - Front stop

– Push-pull rod

14 - Bob weight

– Ball bearing

15 - Lever

– Push-pull rod 1

16 - Push-pull rod

– Two-armed lever

17 - Spring

– Push-pull rod 2

18 - Spring

8 -

Support lever

19 - Sleeve

9 -

Push-pull rod 3

20 - Support lever

10 - Elevator lever

21 - Actuator

11 - Elevator root hinge

Fig. 27-10 Elevator Control System

ELEVATOR AND PITCH TRIM

FLIGHT CONTROLS

2. MAINTENANCE PRACTICES

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

Wrench 9

1 pc

Wrench 8

2 pcs

Wrench 7

2 pcs

Hex key 5

1 pc

Hex key 2.5

1 pc

Solder set

1 pc

Heat gun

1 pc

Shrink tube

ø3.2 x 1.6 mm

Serrated locking washer

ø6.4

Cotter pin

ø1.6 x 25

Cotter pin

ø1.6 x 16

1 pc

Protractor with deflecting pointer

1 pc

Ruler

2 pcs

Adhesive tape

Persons

Tab. 27-4 Recommended tools, materials, persons and documentation

Push rods and levers

Push rods and levers removal:

(a) Remove rudder (Chapter 55-40).

(b) Remove elevators (Chapter 55-20).

nut (16), washer (12) and bolt (9).

(d) Remove cover on baggage bulkhead (13, Chapter 06-00, Fig. 06-4).

(e) Disconnect push rod (3) from support lever (5), by removing nut (16),

washer (12) and bolt (11). Disconnect ground wire (38).

(f)

Disconnect push rod (2) from support lever (5), by removing nut (16),
washer (12) and bolt (11). Disconnect ground wire (39).

(g) Disconnect push rod (2) from bellcrank (6), by removing nut (16),

washer (12) and bolt (9). Disconnect ground wire (36) from socket
(33).

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

Effectivity:

ALL

04. 07. 2019

FLIGHT CONTROLS

(i)

Disconnect spring connector (19, Fig. 27-14) by unscrewing nut (16)
and removing washer (17), bolt (15) and spacer (18).

(j)

Disconnect push rod (1, Fig. 27-11) from bellcrank (6), by removing
nut (16), washer (12) and bolt (9). Disconnect ground wire (34) from
socket (33).

(k) Disconnect push rod (1) from torsion tube (21), by removing nut (16),

washer (12) and bolt (11).

(l)

Remove the root hinge (4), by removing nut (16), washers (12; 13)
and bolt (11).

(m) Remove support lever (5), by removing nut (16), washer (12) and bolt

(8).

(n) Remove bellcrank (6), by removing nut (16), washers (18) and pin

(7).

(o) If necessary, remove front elevator stop by releasing nut (28) and

removing bolt (29). Rear elevator stop could be removed similar way,
by releasing nut (17) and removing bolt (26) and washer (12).

Push rods and levers installation:

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

rivets. Check parallel alignment of bearing ends; on new push rods,
release lock nuts.

(b) Install bellcrank (6, Fig. 27-11) behind baggage bulkhead, by using

pin (7), washers (18) and nut (16).

WARNING

ENSURE

BELLCRANK

(6)

PUT

CORRECT

ORIENTATION!

(16).

(d) Install root hinge (4) to bracket, by using bolt (11), washers (12, 13)

and nut (16).

(e) Connect push rod (3) to root hinge (4), by using bolt (9), washer (12)

and nut (16).

(f)

Connect push rod (3) to support lever (5), by using bolt (11), washer
(12) and nut (16). Connect ground wire (38) to ground wire (39).
If using a new push rod (3):

•

Replace washer (14) and fully screw bearing end (20) and tighten

locking nuts (17).

•

Pay attention to parallel alignment of bearing ends (20).

(g) Connect push rod (2) to support lever (5), by using bolt (11), washer

(12) and nut (16). Connect ground wire (39) to ground wire (38).

(h) Connect push rod (2) to bellcrank (6), by using bolt (9), washer (12)

and nut (16). Connect ground wire (36) to socket (33).
If using new push rod (2):

ELEVATOR AND PITCH TRIM

FLIGHT CONTROLS

•

Replace washer (14) and fully screw bearing ends (20) and

tighten locking nuts (17).

•

Pay attention to parallel alignment of bearing ends (20).

(i)

Connect push rod (1) to bellcrank (6), using bolt (9), washer (12) and
nut (16). Connect ground wire (34) to socket (33).

(j)

Connect push rod (1) to torsion tube (21), using bolt (11), washer
(12) and nut (16). If using new push rod (1):

•

Replace washer (14) and fully screw bearing ends (20) and

tighten locking nuts (17).

•

Pay attention to parallel alignment of bearing ends (20).

•

Install sleeves (20, Fig. 27-14) on push rod (see 2.B.(2)).

•

Perform adjustment of elevator control system (see par. D)

(elevators have to be installed).

(k) Connect spring connector (19, Fig. 27-14) with spacer (18) to lever

(3) using nut (16), washer (17) and bolt (15).

(l)

Carry out test and check:

•

That the castle nuts and pins are secured with cotter pins.

•

If all bolt connections are tight.

•

Plays.

•

Free movement of elevator control system.

•

Neutral position and max displacements.

•

Equal division of threads on push rods.

•

That no foreign objects remain in the aircraft.

Adjustment / Test

– elevator deflections

CONTROL SURFACE DEFLECTIONS

Control surface

Down

Distance measurement point

from the point of rotation

Elevator

28 ±2°

18 ±2°

240 mm

112 ±8 mm

74 ±8 mm

Tab. 27-5 Elevator Deflections

(a) Fix the elevator in neutral position.

(b) Check if distance between PTT button and instrument panel is

245

mm; if it isn’t, adjust length of push rod (1, Fig. 27-11) so that the

distance between PTT button and instrument panel is correct.

NOTE

If it is not possible reach correct distance, screw swivel bearings
(20) at push rod (1). It is necessary to adjust the length of push
rod (2) too.

Effectivity:

ALL

22. 05. 2017

FLIGHT CONTROLS

(d) Put protractor on the trailing edge of elevator.

(e) Set the protracto

r to 0° - starting value of measuring.

(f)

Check deflection values according to the Tab. 27-5.

(g) If deflections are not within range listed in Tab. 27-5, screw stop bolts

(26; 29) to adjust to correct deflections.

(h) Carry out test and check:

•

If all lock nuts are tight.

•

Free plays.

•

Free movement of elevator control system.

•

Neutral position and max. deflections.

•

Equal division of threads on push rods.

•

If trim control operates in all positions

•

That no foreign objects remain in the aircraft.

Effectivity:

ALL

04. 07. 2019

FLIGHT CONTROLS

– Push rod

– Torsion tube

– Push rod

– Hinge

– Push rod

– Bracket

– Root hinge

– Elevator root hinge

– Support lever

– Elevator rear stop

– Bellcrank

– Bolt

– Pin

– Elevator front stop

– Bolt M6 x 48

– Nut

– Bolt M6 x 28

– Bolt M6 x 16

– N/A

– Bolt M4 x 20

– Bolt M6 x 25

– Washer ø4.3 x 12 x 1

– Washer ø6.4 x 12 x 1.6

– Nut M4

– Washer ø6.4 x 10 x 1.6

– Flat terminal

– Serrated locking washer ø6.4

– Ground wire

– Tab washer ø6.4

– Rivet 4 x 8

– Self-locking nut M6

– Ground wire

– Nut M6

– Ground wire

– Washer ø6.4 x 18 x 1.6

– Ground wire

– N/A

– Ground wire

– Bearing end

Fig. 27-11 Push Rods and Levers Removal / Installation (page 2 of 2)

ELEVATOR AND PITCH TRIM

FLIGHT CONTROLS

Pitch trim system

Pitch trim system removal:

(a) Open the

PITCH

circuit-breaker.

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

central tunnel cover (12).

(d) Remove shrink tube and unsolder the cable (2, Fig. 27-14).

(e) Disconnect actuator (1) piston rod from lever (3), by removing nut

(16), washer (17), spacer (14) and bolt (24).

(f)

Hold the actuator (1), remove cotter pin (13), spacers (10; 11),
bushings (12) and pin (9); remove actuator (1) from central tunnel.

(g) Disconnect spring connector (19) by unscrewing the nut (16) and

removing washer (17), bolt (15) and spacer (18).

(h) Remove lever (3), by removing nut (7), washer (8) and bolt (6).

(i)

In case of exchange of springs (4, 5) or sleeve couplings (20),
remove the push rod (25) by unscrewing nuts (16, Fig. 27-11) from
torsion tube (21) and bellcrank (6) and removing washers (12) and
bolts (9, 11). Couplings (20, Fig. 27-14) can be removed from push
rod (24) by drilling out the rivets (located on bottom side of
couplings), removing nuts (22), washers (23) and bolts (21).

Pitch trim system installation:

(a) Clean and lubricate all the movable points and other movable parts

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

(b) Install the lever (3, Fig. 27-14) into bracket on the central tunnel floor,

by using the bolt (6), washer (8) and nut (7).

In the case of installation of original push rod:

spacer (18), washer (17) and nut (16).

(d) Connect springs (4; 5) to the lever (3) and sleeves (20).

(e) Install actuator (1) into the central tunnel, by using pin (9), spacers

(10; 11), bushings (12) and secure with cotter pin (13).

(f)

Attach actuator piston rod to the lever (3), by using bolt (24), spacer
(14), nut (16) and washer (17).

(g) Put on the cable (2) shrink tube, using soldering gun connect wires;

pull the shrink tube over join.

In the case of installation of new push rod:

(h) Install actuator (1) into the central tunnel, by using pin (9), spacers

(10; 11), bushings (12) and secure with cotter pin (13).

(i)

Put on the cable (2) shrink tube, using soldering gun connect wires;
pull the shrink tube over join.

(j)

Attach actuator piston rod to the lever (3), by using bolt (24), spacer
(14), nut (16) and washer (17).

Effectivity:

ALL

04. 07. 2019

FLIGHT CONTROLS

(k) Open the

PITCH

circuit-breaker.

(l)

Put the couplings (20) on the push rod (25) and attach by using
the bolts (21), washers (23) and nuts (22); do not tighten the nuts.

(m) Perform adjustment of elevator control system (see 2.A .(3)).

(n) Move control stick full forward (to the stop) and actuator rod extend

to the max. (150 mm) (Fig. 27-12).

Fig. 27-12 Trim System Adjustment

(o) Set the front sleeve (20, Fig. 27-14) so that between the axis

of the hole on the socket and the axis of the hole on the lever (3) was
length 240

±1 mm (Fig. 27-12); tighten the nuts (22, Fig. 27-14).

(p) Move control stick full rearward (to the stop) and actuator rod full

retract.

(q) Set the rear sleeve (20) so that between the axis of the hole

on the socket and the axis of the hole on the lever (3) was length
272

±1 mm (Fig. 27-13); tighten the nuts (22, Fig. 27-14).

Fig. 27-13 Trim System Adjustment

(r)

Remove push rod (25) (see 2.A.(1)).

ELEVATOR AND PITCH TRIM

FLIGHT CONTROLS

(s) As necessary carefully rotate the front and rear sleeve, so that holes

in the sleeve are aligned with the side face of the ball bearing; do not
move sleeves. Tighten the nuts (22).

(t)

Drill hole diameter 3.2 mm through bottom parts of sleeves and one
side of the push rod; then using riveting tools to rivet parts together.

(u) Connect springs (4; 5) and connector (19) to push rod (25); install

push rod (see par. 2.A.(2)).

(v) Connect connector (19) with springs (4; 5) to the lever (3), by bolt

(15), nut (16), washer (17) and spacer (18).

(w) Check free movement of trim and elevator control system; lever (3)

must not touch the push rod (25).

In both cases:

(x) Check:

•

That the pin is secured with cotter pin.

•

If all bolt connections are tight.

•

That no foreign objects remain in the aircraft.

(y) Install plate behind slotted link (11, Chapter 06-00, Fig. 06-4) and

central tunnel cover (12).

(z) Install pedestal panel (Chapter 27-50, 2.B.(2)).

(aa) Close the

PITCH

circuit-breaker and carry out an operational test;

check trim indication.

Effectivity:

ALL

04. 07. 2019

FLIGHT CONTROLS

– Pitch trim actuator

10 - Spacer

19 - Spring connector

– Cable

11 - Spacer

20 - Sleeve coupling

– Lever

12 - Bushing

21 - Bolt M5x20

– Spring 20/1/4

13 - Cotter pin 1.6 x 16

22 - Self-locking nut M5

– Spring 19/1/4

14 - Spacer

– Washer ø5.3 x 10 x 1

– Bolt M6 x 48

15 - Bolt M6x45

24 - Bolt M6x32

– Self-locking nut M6

16 - Nut M6

For information:

8 -

Washer ø6.4x12x1.6 17 - Washer ø6 x 12 x 0.5 25 - Push rod

9 -

18 - Spacer

26 - Bracket

Fig. 27-14 Trim System Removal / Installation

ELEVATOR AND PITCH TRIM

FLIGHT CONTROLS

Bob weight

Bob weight removal:

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

(b) Disconnect push-pull rod (3, Fig. 27-15) from torsion tube (11), by

removing nut (5), washer (8) and bolt (9).

remove lever (1) from central tunnel.

(d) Disconnect push-pull rod (3) from lever (1), by removing nut (5),

washer (8), spacer (10) and bolt (7).

(e) As necessary, remove weight (2) from lever (1), by removing nuts

(5), washers (8) and bolts (7).

Bob weight installation:

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

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

(b) Before assembling check lever for cracks.

by using the bolts (7), washers (8) and nuts (5).

(d) Attach push-pull rod (3) to the lever (1), by using bolt (7), spacer (10),

nut (5) and washer (8).

(e) Install the lever (1) into the central tunnel, by using the bolt (4),

washers (6) and nut (5).

(f)

Attach push-pull rod (3) to the torsion tube (11), by using bolt (9), nut
(5) and washer (8).

(g) Check:

•

If all bolt connections are tight.

•

That no foreign objects remain in the aircraft.

(h) Install pedestal panel (Chapter 27-50, 2.B.(2)).

Effectivity:

ALL

04. 07. 2019

FLIGHT CONTROLS

– Lever

8 -

Washer ø6.4 x 12 x 1.6

– Bob weight

9 -

Bolt M6 x 25

– Push-pull rod

10 - Spacer

– Bolt M6 x 128

Torsion tube

– Nut M6

For information:

– Washer ø6.4 x 12 x 0.5

12 - Central tunnel side

7 -

Bolt M6 x 48

Fig. 27-15 Bob Weight Removal / Installation

FLAPS

FLIGHT CONTROLS

27-50 FLAPS

1. DESCRIPTION

The wing flaps are operated manually by a lever (1, Fig. 27-16) on the pedestal panel
between pilot and co-pilot. Wing flaps lever moves in the slotted link (2) that
determinates four positions:

FLAPS 0

- Retracted

(0°),

FLAPS 1

Takeoff position (15°),

FLAPS 2

- Mid-

position (24°),

FLAPS 3

Fully extended position (35°).

Movements from wing flap lever are transferred through the push-pull rod 1 (3) and
bellcrank (4) to the flap's torsion tube (5). Flap’s torsion tube is fixed in three sliding
bearings (6) which are attached to the central section auxiliary spar (middle bearing)
and outer ribs (left and right bearing). It makes mechanical interconnection between
left and right wing flap. Torsion tube is connected with the wing flap lever (7) by means
of push-pull rods (8) with fork at the one and adjustable bearing end at the other one.
Wing flap lever is fixed at the wing flap (9).

Gas strut (10) installed in the flap control system reduces

pilot’s operating force during

extending/retracting of wing flaps. The gas strut is located in the baggage compartment
and attached to the central tunn

el and flap’s torsion tube. It is protected by laminate

cover (Chapter 06-00, Fig. 06-4).

The pedestal panel (2, Fig. 27-16) is attached on top of central tunnel between seats.
On the pedestal panel are located: brake lever, wing flap lever and trim switches. Under
the cover in the central tunnel are the elevator and wing flap push rods, rudder control
cables, brake system, electrical wires, etc.

WT9 Dynamic LSA. AIRCRAFT MAINTENANCE MANUAL (AS-AMM-01-000, 22. 05. 2017) - page 18