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WT9 Dynamic LSA. AIRCRAFT MAINTENANCE MANUAL (AS-AMM-01-000, 22. 05. 2017) - page 19

Effectivity:

ALL

04. 07. 2019

FLIGHT CONTROLS

– Lever

6 -

Bearing

– Pedestal panel

7 -

Wing flap lever

– Push-pull rod 1

8 -

Push-pull rod

– Bellcrank

9 -

Wing flap

– Torsion tube

10 - Gas strut

Fig. 27-16 Wing Flap Control System

FLAPS

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 8

1 pc

Screwdriver

1 pc

Puller on small pins M4

1 pc

Pliers

1 pc

Serrated locking washer

ø6.4

2 pcs

Cotter pin

ø1.6 x 25

2 pcs

Knife

1 pc

Vaseline

Silicone

Protractor with deflecting pointer

1 pc

Adhesive tape

Ruler 50 cm

1 pc

Persons

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

Flap control system

Flap control system removal:

(a) Remove wings (Chapter 57-10)

(b) Disconnect push rod (3, Fig. 27-18) from torsion tube (1), by

removing nut (12), washer (13) and bolt (7).

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

(e) Disconnect bellcrank (2) from torsion tube (1), by removing nut (11),

washer (13), bolt (8) and remove ground wire (20).

(f)

In baggage compartments, remove covers of torsion stick (with knife,
Velcro attachment) and gas strut cover.

(g) Remove gas strut (18).

(h) Remove cover on wing root central section with knife.

(i)

Disassemble all sliding bearings (6), by removing nuts (11), washers
(13; 14; 15) and bolts (5; 9).

(j)

On right side of centre section, carefully pull out torsion tube (1)
through access hole.

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FLIGHT CONTROLS

Flap control system installation:

(a) Before installation check main parts for cracks and condition of rivets

on push rod.

(b) Carefully rotate and slide torsion tube (1, Fig. 27-18) from right side

of centre section wing root through all holes to other side (wings have
to be removed).

on middle insert and sides carbon holders, by using bolts (5; 9),
washers (13; 14; 15) and nuts (11).

NOTE

Tighten nuts (11) so that the torsion tube (1) rotates easily.

(d) Stick cover on centre section roots with silicone (remove old

silicone).

(e) Connect bellcrank (2) to torsion tube (1), by using bolt (8), washer

(13) nut (11) and ground wire (20).

(f)

Install push rod and pedestal panel (Chapter 27-50, 2.B.(2)).

(g) In right baggage compartment attach gas strut (18) to torsion tube

lever and ball joint.

CAUTION

GAS STRUT HAS TO BE ORIENTED WITH VALVE SIDE UP
AND PISTON ROD DOWN.

(h) Install gas strut cover.

(i)

Attach covers of torsion tube.

(j)

Install wings (Chapter 57-10).

(k) Connect push rod (3) to torsion tube (1), by using bolt (7), washer

(13) and nut (12).

(l)

Connect push rod (3) to wing flap hinge, by using pin (4) and cotter
pin (17). If using new push rod(s) (3):

•

Set wing flap lever to position 0 (flaps retracted).

•

Flap trailing edges must be aligned with centre section trailing

edge (a preload is created in the wing flap control system).

•

If previous point isn´t not fulfilled, disconnect pin (4), release lock
nut (10) and screw push rod (3) to adjust to correct length.
Replace washer (16) and tighten lock nut (10); check rod end in
safety.

•

Secure pin (4) with cotter pin (17).

(m) Connect second push rod (3).

FLAPS

FLIGHT CONTROLS

(n) Carry out test and check:

•

That the pins are secured with cotter pins.

•

If all bolt connections are tight.

•

Free plays.

•

Free movement of flap control system.

•

If deflections of wing flaps are symmetrical.

•

Deflections (Tab. 27-8).

•

Push rod swivel motion in both wing flap positions for binding

(retracted and fully extended) (Fig. 27-17); if binding occurs,
realign rod end bearing.

•

That no foreign objects remain in the aircraft.

Fig. 27-17 Swivel Motion of Push Rod

Adjustment / test - flaps deflections:

Both wing flaps have to be adjusted simultaneously. Described is adjusting
of the right side. The process for the left side is mirrored.

CONTROL SURFACE DEFLECTIONS

Control surface

Deflection

Distance measurement point

from the point of rotation

Wing flaps

FLAPS 1

15 ±2°

76 ±6 mm

295 mm

(Root rib of the outer wing)

FLAPS 2

24 ±2°

120 ±6 mm

FLAPS 3

35 ±2°

181 ±6 mm

Maximum deflection difference between both flaps: ±2°/±6 mm

Tab. 27-8 Wing Flap Deflections

Effectivity:

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22. 05. 2017

FLIGHT CONTROLS

(a) Set protractor on trailing edge of wing flap root.

(b) Set wing flaps to fully retracted position.

(c)

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

(d)

Check deflections at first position 15°, second position 24° and third
position 35°, see Tab. 27-8.

(e) Check if deflections are symmetrical on both wing flaps.

(f)

If deflections are not within range listed in Tab. 27-8, remove cotter
pin (17, Fig. 27-18) and pin (4), release lock nut (10), use new
washer (16) and screw push rod (3) to set correct length.

(g) Check if push rod fork (3) is parallel with swivel bearing (19).

(h) Tighten lock nut (10).

(i)

Connect push rod (3) to wing flap with pin (4) and secure with cotter
pin (17).

(j)

Carry out test and check:

•

That the pins are secured with cotter pins.

•

Free movement of flap control system.

•

Deflections.

•

Push rod swivel motion in both wing flap positions for binding

(retracted and fully extended) (Fig. 27-17); if binding occurs,
realign rod end bearing.

•

That no foreign objects remained in the aircraft.

FLAPS

FLIGHT CONTROLS

– Torsion tube

11 - Self-locking nut M6

– Bellcrank

12 - Nut M6

– Push-pull rod

13 - Washer

ø6.4 x 12 x 1.6

– Pin

14 - Washer

ø6.4 x 18 x 1.6

– Bolt M6 x 52

– Washer ø6.4 x 12 x 0.5

– Sliding bearing

– Serrated locking washer ø6.4

– Bolt M6 x 19

– Cotter pin ø1.6 x 25

– Bolt M6 x 28

– Booster

– Bolt M6 x 60

– Swivel bearing

10 - Nut M6

– Ground wire

Fig. 27-18 Flap Control System Removal / Installation

Effectivity:

ALL

04. 07. 2019

FLIGHT CONTROLS

Pedestal panel

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

Wrench 10

2 pcs

Wrench 8

1 pc

Screwdriver 10

1 pc

Philips screwdriver

1 pc

Vaseline

Persons

Tab. 27-7 Recommended tools, materials, persons and documentation

Pedestal panel removal:

(a) Remove upholstery (3, Fig. 27-19).

(b) Remove arm rest (2) by unscrewing the bolts (7).

handle (5).

(d) Disconnect the push rod (4) from bellcrank (17) by unscrewing nut

(15) and removing bolt (11) with washer (12).

(e) Unscrew the bolts (7) and carefully lift the pedestal panel (1).

(f)

Disconnect the connector (18).

(g) Disconnect push rod (4) from main cover (1), by unscrewing nut (15)

and removing washers (12; 13) with bolt (10).

(h) Remove pedestal panel (1).

Pedestal panel installation:

(a) Thoroughly clean and lubricate bearings on push rods with Vaseline

before each assembling (Chapter 12-20).

NOTE

If using new push rod (4, Fig. 27-19), fully screw swivel bearings
and tighten counter nuts. Check parallelism of swivel bearings.

(b) Connect push rod (4) to pedestal panel (1), using bolt (10), washers

(12; 13) and nut (15).

and nut (15).

FLAPS

FLIGHT CONTROLS

WARNING

CHECK CONTROL TUNNEL VERY CAREFULLY FOR
FOREIGN OBJECTS AND TOOLS AFTER REASSEMBLY!

(d) Connect the connector (18).

(e) Place the pedestal panel (1) to the tunnel and install attaching bolts

(7).

(f)

Install the brake handle (5) by using bolt (9), nut (16) and washer
(14),

(g) Place the arm rest (2) to the tunnel and install attaching bolts (7).

(h) Install upholstery (3).

(i)

Carry out test and check:

•

If all bolt connections are tight.

•

Free movement of control levers.

•

That no foreign objects remain in the aircraft.

Effectivity:

ALL

04. 07. 2019

FLIGHT CONTROLS

– Slotted link

– Bolt M6 x 28

– Arm rest

– Bolt M6 x 19

– Upholstery

– Washer ø6.4 x 12 x 1.6

– Push rod

– Washer ø6.4 x 10 x 1.6

– Brake handle

– Washer ø5.3 x 10 x 1

– Intentionally left blank

– Self-locking nut M6

– Bolt M4 x 12

– Self-locking nut M5

– Intentionally left blank

– Bellcrank

– Bolt M5 x 30

– Connector

Fig. 27-19 Pedestal panel Removal / Installation

CONTENTS

FUEL

28 FUEL

CONTENTS

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

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

TROUBLESHOOTING ............................................................... 5

28-10

STORAGE ......................................................................... 7

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

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

Drain valve ........................................................................ 7

28-20

DISTRIBUTION ................................................................. 9

DESCRIPTION .......................................................................... 9

MAINTENANCE PRACTICES ................................................. 10

Electric fuel pump ............................................................ 10

One-way valve ................................................................. 12

Fuel filter .......................................................................... 13

Fuel strainer .................................................................... 16

Fuel selector .................................................................... 18

Fuel lines ......................................................................... 21

Ventilation line ................................................................. 26

28-40

INDICATING ................................................................... 29

DESCRIPTION ........................................................................ 29

MAINTENANCE PRACTICES ................................................. 29

SV-D1000 display ............................................................ 29

Standby fuel pressure indicator ....................................... 29

Fuel level sensor ............................................................. 30

Fuel pressure sensors ..................................................... 34

Fuel flow transducer ........................................................ 39

GENERAL

FUEL

28-00 GENERAL

1. INTRODUCTION

Fuel is supplied to the engine in dependence from fuel selector position (

LEFT

RIGHT

OFF

) (22, Fig. 28-1). From fuel tanks (16; 17; 18; 19) the fuel flows through the fuel

strainers (23) and fuel filters (21) to the fuel selector (22) inlets. From the fuel selector
the fuel flows  through the electric  fuel  pump (12)  with  the by-pass check  valve  (13)
to  engine  driven  fuel  pump  (1)  and  then  to  distributor  inlet  (4).  One  of  distributor's
outlets  is  connected  to  carburettors  (2;  3)  through  the  fuel  flow  transducer  (7)  and
3-way distributor (5). Fuel flow transducer is installed the way to measure only the fuel
consumed by engine. Second one is fitted with restrictor jet (6) to which return line is
connected. Return line leads back to the left fuel tank (17).

Wing fuel tanks (16; 19) are connected with the fuselage tanks (17; 18) using simple
hose connection with clamps. Fuel tanks are vented from the highest point and
discharge through the hoses protruding under aircraft through the fuselage skin inside
of central tunnel.

There  is  fuel  level  sensor  (15)  in  the  both  left  and  right  fuel  tank.  Fuel  level  sensor
is installed in  the root rib of  fuselage fuel tanks. Signal from the fuel level sensor is
carried to the engine monitoring system unit Dynon  SV-EMS 220 (8) and from there
to the Dynon SkyView SV-D1000 (10).

Fuel  pressure  sensor  (9)  and  standby  fuel  pressure  indicator  (11)  are  installed
in the fuel system and connected through the 3-way distributor (5) with restrictor jets
in  its  outlets  to  the  4-way  distributor  (4).  Both  check  the  actual  pressure  in  the  fuel
supply line.  Signal from the fuel pressure sensor is carried to the engine monitoring
system unit Dynon EMS 220 (8) and from there to the Dynon SkyView SV-D1000 (10).
Exceeding  of  fuel  pressure  limit  value  is  signalized  by  red  warning  lamp

EMS

on the instrument panel (Chapter 39).

Wiring diagram of fuel system components is described in the Aircraft Wiring Manual
(Doc. No. AS-AWM-01-000).

Effectivity:

ALL

12. 06. 2020

FUEL

– Engine fuel pump

– Fuel pressure sensor

– LH centre section fuel tank

– LH carburetor

– SkyView SV-D1000

– RH centre section fuel tank

– RH carburetor

– Standby fuel pressure indicator 19 – RH wing fuel tank

– 4-way distributor

– Electric fuel pump

– Drain valve

– 3-way distributor

– One-way valve

– Fuel filter

– Restrictor jet

– Filler cap

– Fuel selector

– Fuel flow transducer 15 – Fuel level sensor

– Fuel strainer

– SV-EMS 220

– LH wing fuel tank

Fig. 28-1 Fuel System Scheme

GENERAL

FUEL

2. TROUBLESHOOTING

TROUBLE

POSSIBLE CAUSE

REMEDY

Filler cap leaks.

Filler cap improperly
installed.

Install filler cap properly.

Seal improperly installed.

Replace fuel cap seal.

Deteriorated seal.

Replace fuel cap seal.

Fuel connector(s) leak.

Loose connector(s).

Inspect and tighten
connector(s).

Defective seals.

Replace seals.

Defective thread.

Replace threaded
component.

Insufficient fuel flow.

Restricted fuel filter.

Replace filter.

Defective engine fuel
pump.

Replace pump.

Defective fuel pressure
sensor.

Replace pressure sensor.

Cracked fuel line.

Replace line.

Fuel quantity indicator
reading incorrect.

Defective fuel sensor.

Replace sensor.

Defective fuel quantity
indicator.

Replace indicator.

Incorrectly adjusted fuel
sensor.

Adjust sensor.

Faulty fuel system wiring.

Repair/Replace wire(s).

No fuel flow to the engine
fuel pump.

Fuel selector valve not in
the

position.

Turn selector valve

Fuel tanks empty.

Fill tanks.

Fuel line disconnected or
broken.

Repair or replace line.

Defective fuel selector
valve.

Replace selector valve.

Fuel line plugged.

Remove obstruction.

Fuel starvation after start
up.

Partial fuel flow from
proceeding causes.

See remedies from above

Malfunction of engine-
driven fuel pump or fuel
system.

Replace pump.

Effectivity:

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12. 06. 2020

FUEL

TROUBLE

POSSIBLE CAUSE

REMEDY

Fuel starvation after start
up (cont.).

Fuel vents plugged.

Remove obstruction.

Water in fuel.

Remove water.

Erratic fuel quantity
indicator readings.

Defective fuel quantity
indicator

Replace indicator

Defective fuel sensor

Replace fuel sensor

Fuel quantity indicator
indicates inaccurate fuel
level.

Fuel system calibration.

Calibrate fuel system.

Defective fuel quantity
indicator or sensor.

Replace indicator or
sensor.

No fuel quantity indication

Fuel tanks empty

Fill with approved fuel

Loose connections.

Tighten connections.

Defective fuel quantity
indicator or sensor

Replace indicator or
sensor.

STORAGE

FUEL

28-10 STORAGE

1. DESCRIPTION

The aircraft has integral fuel tanks with a total capacity of approximately 126 liters.

The integral fuel tanks are located in the forward box of the  fuselage central section
and both halves of wing. The wing and central section tanks are connected by a simple
hose connection with clamps. There is one large diameter hose between tanks, which
serves  the  fuel  from  the  wing  tanks  to  central  section  tanks.  There  are  two  small
diameter  hoses,  one  of  them  is  venting  line  of  wing  tank  and  second  one  connects
the both tanks (air connection).

The integral fuel tanks are covered by a special paint resistive to fuel with a less
electrical resistance. There is a rib in each tank for preclusion of a rapid fuel flowage
during the flight manoeuvres.

The fuel tank filler caps are located on a wing upper surface. The drain valves are
located the lowest point of each tank.

2. MAINTENANCE PRACTICES

Drain valve

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 16

1 pc

O-ring

ø18.9 x 1.8

1 pc

Loctite 243

Persons

Tab. 28-1 Recommended tools, materials, persons and documentation

WARNING

GROUND THE EXHAUST PIPE OUTLET AND FUEL SERVICE
EQUIPMENT PRIOR TO AIRCRAFT REFUELLING/DEFUELING!

ENGINE IGNITION MUST BE SWITCHED OFF. DISCONNECT
NEGATIVE TERMINAL OF AIRCRAFT BATTERY.

DRAINING ALL FUEL FROM THE FUEL SYSTEM IS NOT
POSSIBLE, BE CAREFUL DURING DISASSEMBLING THE FUEL
SYSTEM!

(1) Drain valve removal:

Make sure that the

IGNITION

switches are set to

OFF

Remove engine cowlings (Chapter 71-10).

Disconnect negative terminal of battery (Chapter 24-30).

Effectivity:

ALL

12. 06. 2020

FUEL

Electrically ground the aircraft (use the exhaust pipe outlet)

to the grounding point.

Drain fuel tanks (Chapter 12-10).

Unscrew and remove the drain valve (1, Fig. 28-2) from wing.

Discard O-ring (2).

(2) Drain valve installation:

Make sure that the

IGNITION

switches are set to

OFF

Inspect drain valve for contaminates; remove contaminates

as necessary.

Apply Loctite 243 and screw the drain valve (1, Fig. 28-2) with a new

O-ring (2).

Check if drain valve is firmly secured and sealed.

Connect negative terminal of the battery (Chapter 24-30).

Replenish the fuel system (Chapter 12-10).

Remove the ground cable from the aircraft.

Carry out engine ground test; check the drain valve function and fuel

system for leaks.

– Drain valve

For information:

– O-ring

ø7.66 x 1.78

– Wing bottom surface

Fig. 28-2 Drain Valve Removal / Installation

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