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

GENERAL

EQUIPMENT/

FURNISHINGS

25-00 GENERAL

1. INTRODUCTION

This chapter describes equipment and furnishing in the flight compartment. Chapter
25-10 includes the pilot and co-pilot seats, safety harnesses and safety belts.

Chapter 25-60 gives the data for the Emergency Parachute System (EPS) and
Emergency Locator Transmitter (ELT).

FLIGHT COMPARTMENT

EQUIPMENT/

FURNISHINGS

25-10 FLIGHT COMPARTMENT

1. DESCRIPTION

Pilot and co-pilot's seats are integral part of interior arranged side-by-side and consist
of removable laminate seats (2, Fig. 25-1) and backrest, which is bonded with central
tunnel and fuselage. Seats are covered with upholstery seats (1).

Seats are equipped with 4-point safety harnesses (3). Safety harnesses consist
of two lap belts, two shoulder belts and a safety harness lock. Lap belts are attached
to the central tunnel and interior sidewalls and shoulder belts are attached to the top
of backrest. Length of each belt is adjustable.

– Upholstery seat

– Safety harness

– Laminated seat

Fig. 25-1 Flight Compartment Furnishing Locations

Effectivity:

ALL

22. 05. 2017

EQUIPMENT/
FURNISHINGS

2. MAINTENANCE PRACTICES

Seats

Described is procedure for removal of left laminated seat.

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

Screwdriver 10

1 pc

Persons

Tab. 25-1 Recommended tools, materials, persons and documentation

(1) Seat removal:

(a) Remove the upholstery seat (1, Fig. 25-2).

(b) Remove bolts (3) and take out the laminated seat (2).

(2) Seat installation:

(a) Place the seat (2, Fig. 25-2) into the fuselage and install bolts (3).

(b) Install the upholstery seat (1).

– Upholstery seat

– Bolt M5 x 12

– Laminated seat

Fig. 25-2 Seat Removal / Installation

FLIGHT COMPARTMENT

EQUIPMENT/

FURNISHINGS

Safety harnesses

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 13

2 pcs

Persons

Tab. 25-2 Recommended tools, materials, persons and documentation

(1) Safety harness removal:

(a) Remove the seat upholstery (see par. 2.A.(1)).

(b) From the attachment bracket in the backrest, unscrew the nut

(4, Fig. 25-3), remove the washers (3), shoulder belt bracket (2) and
bolt (1).

(1), remove the lap belt bracket (5) and washer (6).

(d) Remove other safety belts.

(2) Safety harness installation:

(a) Check safety harnesses for wear, cracks and damage; check

operation of the safety harness lock.

NOTE

Tighten bolts (1, Fig. 25-3) so that it is only possible to rotate belt
brackets with force.

(a) Put the lap belt bracket (5) on the bolt (1), insert the washer (6) and

install into the attachment bracket on side of the seat.

(b) Put the shoulder belt bracket (2) on the bolt (1), insert the bolt into

the attachment bracket in the backrest, insert the washers (3), screw
and tighten the nut (4).

Effectivity:

ALL

04. 07. 2019

EQUIPMENT/
FURNISHINGS

– Bolt M8 x 32

– Self-locking nut M8

– Shoulder belt bracket

– Lap belt bracket

– Washer

8.4 x 24 x 2

– Washer

20 x 8 x 4

Fig. 25-3 Safety Harness Removal / Installation

CARGO COMPARTMENTS

EQUIPMENT/

FURNISHINGS

25-50 CARGO COMPARTMENTS

1. DESCRIPTION

Front baggage compartment (1, Fig. 25-4) is located in front of main spar. Rear
baggage compartment (2) is situated between backrest and baggage bulkhead.
Central tunnel passes through the baggage compartment and divides it in two
sections. Each section of baggage compartment has two front (3) and two rear (4)
attaching points to which the baggage can be fixed with fastening straps and
baggage net.

In the rear baggage compartment is located flap torsion tube equipped with
a laminate cover (7; 8, Chapter 06-00, Fig. 06-4).

– Front baggage compartment

– Front attaching points

– Rear baggage compartment

– Rear attaching points

Fig. 25-4 Baggage Compartments

EMERGENCY

EQUIPMENT/

FURNISHINGS

25-60 EMERGENCY

1. DESCRIPTION

The aircraft is equipped with emergency parachute system (EPS) MAGNUM 601
S-LSA from the company STRATOS 07 spol. s r. o.

Parachute container (1, Fig. 25-5) is located behind instrument panel and is attached
to the board. Two main straps (3) are attached to the stiffened areas at firewall and
stabilizing strap is attached to the steel cable (5) (bonded in the structure of right
fuselage shell). Main and stabilizing straps are through a carabine attached to the
parachute strap.

Extraction device (rocket) (2) is attached in the laminate holders that are bonded to
the firewall. It is connected with the parachute extraction cable. Rocket is connected
to an actuator (4) installed at the central console by a Bowden cable. Actuator is
secured by protector of EPS actuator from unintentional activation of rocket.

NOTE

For more details refer to “MANUAL FOR MOUNTING AND USE OF RESCUE
BALLISTIC PARACHUTE SYSTEMS SERIES MAGN

UM”, latest issue.

The aircraft is equipped with ELT KANNAD 406 AF-COMPACT / KANNAD
AF INTEGRA.

The KANNAD 406 AF-

COMPACT is a FAA TSO’d approved, EASA ETSO’d

approved, 406 MHz, Automatic Fixed (AF) Emergency Locator Transmitter. The ELT
KANNAD 406 AF-COMPACT can be activated either automatically when the crash
occurs (by a shock sensor) or manually (by a switch on the transmitter itself or on a
remote control unit on the instrument panel). The ELT transmits emergency signals
on two frequencies:

•

406 MHz (Cospas-Sarsat frequency) for precise pinpointing and identification
of the aircraft,

•

121.5 MHz used for homing in the final stages of the rescue operations.

The energy to the units is provided by a battery pack composed of a LiMnO

two-

element battery. Until the battery expiry date, the duration of the 121.5 MHz
transmission is over 48 hours at -

20°C. As it is therefore preferable to keep the

battery power for 121.5 MHz homing frequency transmission for the rescue
operations, in compliance with Cospas-Sarsat specifications, the 406 MHz
transmission is deliberately stopped after 24 hours to extend the 121.5 MHz
transmission for as long as possible.

The ELT KANNAD 406 AF-COMPACT consists of the unit (6, Fig. 25-5) which is
installed in the baggage compartment and the remote control unit which is installed
on the right side of the instrument panel.

The external antenna (7) is installed on the

bracket on the right part of the fuselage behind the baggage compartment and is
accessible through a baggage bulkhead cover access panel at the base of the
baggage compartment bulkhead.

Effectivity:

ALL

29. 01. 2020

EQUIPMENT/
FURNISHINGS

The KANNAD AF INTEGRA is a FAA TSO’d approved, EASA ETSO’d approved,
406 MHz, Automatic Fixed (AF) Emergency Locator Transmitter with G-Switch
sensor. This ELT Transmitter has internal back-up antenna inside.

Integra’s internal

antenna provide the unique ability to transmit and send both aircraft identification
data and GPS position even when the crew remove it from the aircraft. The ELT
KANNAD AF INTEGRA can be activated either automatically when the crash occurs
(by a shock sensor) or manually (by a switch on the transmitter itself or on a remote
control unit on the instrument panel). The ELT transmits emergency signals on two
frequencies:

•

406 MHz (Cospas-Sarsat frequency) for precise pinpointing and identification
of the aircraft,

•

121.5 MHz used for homing in the final stages of the rescue operations.

The energy to the units is provided by a battery pack composed of a LiMnO

two-

element battery. Until the battery expiry date, the duration of the 121.5 MHz
transmission is over 48 hours at -

20°C. As it is therefore preferable to keep the

The ELT KANNAD AF INTEGRA consists of the unit (6, Fig. 25-5) which is installed
in the baggage compartment and the remote control unit which is installed on the
right side of the instrument panel.

The external antenna (7) is installed on the bracket

on the right part of the fuselage behind the baggage compartment and is accessible
through a baggage bulkhead cover access panel at the base of the baggage
compartment bulkhead.

Wiring diagram of

ELT´s are described in the Aircraft Wiring Manual

(Doc. No. AS-AWM-01-000).

EMERGENCY

EQUIPMENT/

FURNISHINGS

NOTE

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).

– Parachute

– Steel cable

– Rocket

– ELT unit

– Main strap

– ELT antenna

– Actuator

Fig. 25-5 Emergency Equipment

Effectivity:

ALL

29. 01. 2020

EQUIPMENT/
FURNISHINGS

2. MAINTENANCE PRACTICES

Emergency parachute system

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 22

1 pc

Wrench 8

1 pc

Socket set 10, 17

1 pc

Hex key 3

1 pc

Screwdriver 10

1 pc

Knife

1 pc

Cooper wire

ø0.5 mm with sealing

1 pc

Loctite 243

Persons

Manual for Mounting and Use of Rescue Ballistic Parachute
Systems Series Magnum

Tab. 25-3 Recommended tools, materials, persons and documentation

WARNING

DURING

SERVICE

AND

REPAIR

WORK

BEWARE

ACTIVATING THE BALLISTIC RECOVERY SYSTEM!

ENGINE IGNITION MUST BE SWITCHED OFF!

(1) Emergency parachute system removal:

(a) Make sure that the

IGNITION

switches are set to

OFF

(b) Remove upper engine cowling (Chapter 71-10).

(d) Open parachute container (1, Fig. 25-7) and unscrew nuts on snap

hooks (3; 4); disconnect parachute cable (15) from snap hook (4) and
parachute strap (17) from snap hook (3).

NOTE

Be careful not to break the seal (16) when undoing small snap
hook (4).

(e) Under rescue system board cut all ropes (18) and remove parachute

container (1) from the aircraft.

EMERGENCY

EQUIPMENT/

FURNISHINGS

(f)

From engine compartment unscrew the nuts (26), remove washers
(25) and pull out the U bolts (10) from interior.

(g) Cut cable ties (28) fixing the main straps (5; 7) and stabilizing strap

(6) and remove the straps (5; 6; 7) from the aircraft.

(h) Remove cable ties (27) securing the bowden from actuator to rocket.

WARNING

DURING INCORRECT MANIPULATION WITH UNLOCKED
ACTUATOR

THERE

DANGER

ROCKET

ACTIVATION! AVOID OF ROUGH MANIPULATION IF
ACTUATOR

BOWDEN

HAS

JAMMED

DURING

REMOVING!

(i)

Cut seal and open actuator protector (13).

(j)

Unscrew bolts (21), and pull out lateral actuator handle (12).

(k) Unscrew bolts (20), remove actuator protector (13), Velcro strap and

unlock actuator (11) by removing of lock (19).

(l)

Very carefully remove actuator (11) from the rear of central
instrument panel, simultaneously carefully pull out the bowden; after
the actuator is removed, immediately lock the actuator using lock
(19).

(m) Put the lateral actuator handle (12) back on and secure with bolts

(21).

(n) Unscrew nuts (24), remove washers (22; 23), holder (9) and pull out

rocket (2) with actuator (11).

(o) If necessary, disassemble the safety guard:

•

Remove the cotter pin (31) and washer (33).

•

Remove the pin (29), spring (30) and safety guard holder (32).

(2) Emergency parachute system installation:

(a) Before installation ensure, that the emergency parachute system

actuator (11, Fig. 25-7) is locked!

(b) Insert the rocket (2) with bowden, from cockpit through opening of

rescue system board; put washers (23), rocket (2), holder (9),
washers (22) and tight nuts (24).

NOTE

Min. radius of bowden has to be 140 mm.

(d) Use cable ties (27) to attach bowden to fuel hose and to bowden

harness.

Effectivity:

ALL

29. 01. 2020

EQUIPMENT/
FURNISHINGS

WARNING

DURING INCORRECT MANIPULATION WITH UNLOCKED
ACTUATOR

THERE

DANGER

ROCKET

ACTIVATION! AVOID OF ROUGH MANIPULATION IF
ACTUATOR

BOWDEN

HAS

JAMMED

DURING

INSTALLATION!

(e) Unscrew bolts (21) and unscrew lateral actuator handle (12).

(f)

Unlock actuator (11) by removing of lock (19) and carefully insert
handle to central instrument panel from the rear side; immediately
lock the actuator using lock (19). Stick on Velcro fastener.

(g) If necessary, assemble the safety guard:

•

Place the actuator protector (13) and spring (30) to the holder

(32).

•

Install pin (29), washer (33) and cotter pin (31).

(h) Place the assembled safety guard (13) and screw on bolts (20);

secure with Loctite 243.

(i)

Put lateral handle (12) and tighten the bolts (21); secure with Loctite
243.

(j)

Close actuator protector (13) and secure it with copper lockwire
and seal.

(k) Pass strap (6) through cable (8) and pull tight (Fig. 25-6).

Fig. 25-6 Strap Pass through Cable

(l)

Properly loop straps (5; 6; 7, Fig. 25-7) and secure them with cable
ties (28); do not secure straps to aircraft yet.

NOTE

If the straps are still looped, it is not necessary repack again.

(m) Connect U bolt (10) to strap loop (5); secure loop with cable tie (28).

(n) Attach U bolt with strap to left side of firewall, put washers (25) and

tighten the nuts (26).

(o) Route strap (5)

over all cables and bowdens

to right side of aircraft.

(p) Secure looped strap (5) to rescue system board with one cable tie

(28).

EMERGENCY

EQUIPMENT/

FURNISHINGS

(q) Connect second U bolt (10) to second strap loop (7); secure loop

with cable tie (28).

(r)

Attach U bolt with strap to right side of firewall, put washers (25) and
tighten nuts (26).

(s) Pass ropes (18) through loops on the parachute container (1) and

place parachute container (1) on rescue system board. Strap (5)
must be routed between parachute container (1) and firewall.
Securing ropes (18) pass through holes in rescue system board, tie
and cut off the surplus.

(t)

Connect strap loops (5; 6; 7) with big snap hook (3); secure snap
hook with Loctite 243.

(u) Connect parachute cable (15) and cable of rocket (14) with small

snap hook (3); secure snap hook with Loctite 243. Close the flap on
the parachute container (1).

(v) Secure straps (6; 7) to rescue system board with one cable tie (28).

(w) If is needed, secure all straps and wires with necessary amount of

cable ties (28).

(x) Install cover (7, Chapter 06-00, Fig. 06-3) and tighten bolts.

(y) Install upper engine cowling (Chapter 71-10).

(z) Carry out test and check:

•

If all bolt connections are tight.

•

That all nuts are tight.

•

If straps are properly aligned.

•

If handle is properly locked.

•

If components of ballistic rescue system are secured.

•

Equal division of the threads on the push rods.

•

That no foreign objects remain in the aircraft.

EMERGENCY

EQUIPMENT/

FURNISHINGS

– Parachute container

– Lateral actuator handle

– Washer ø6.4 x 18 x 0.6

– Rocket

– Actuator protector

– Self-locking nut M6

– Big snap hook

– Cable of rocket

– Washer ø10.5 x 30 x 2.4

– Small snap hook

– Parachute cable

– Self-locking nut M10

– Left strap 2.4 m

– Seal

– Cable tie 3.2

– Stabilizing strap 1 m

– Parachute strap

– Cable tie 2.6

– Right strap 2.4 m

– Rope ø3 x 400

guaranteed strength

180 daN (kg)

– Pin ø 5

– Cable

– Lock

– Spring

– Holder

– Hex bolt M5 x 16

– Cotter pin 1.2 x 10

– U bolt

– Allen bolt M4 x 10

– Safety guard holder

– Actuator

– Washer ø6.4 x 12 x 0.6

– Washer ø5.3 x 10 x 1

Fig. 25-7 Emergency Parachute System Removal / Installation (page 2 of 2)

Effectivity:

ALL

29. 01. 2020

EQUIPMENT/
FURNISHINGS

Emergency locator transmitter (ELT)

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 3/4 in

1 pc

Wrench 5.4

1 pc

Philips screwdriver

1 pc

Persons

Tab. 25-4 Recommended tools, materials, persons and documentation

(1) ELT unit removal:

(a) Set switch on the unit to

OFF

position.

(b) Disconnect connectors (4, Fig. 25-8) from the unit.

(d) Remove the unit (1) from the bracket (2).

(2) ELT unit installation:

(a) Install the unit (1, Fig. 25-8) on the bracket (2) with "Flight direction"

arrow pointed towards the front of the aircraft.

(b) Slide the self-stripping strap (3) through the buckle. Ensure the buckle

is correctly positioned (indifferently on right or left side of ELT)
regarding the horizontal center line of ELT.

CAUTION

INCORRECT  TIGHTENING  OF  THE  HOOK  AND  LOOP
FASTENER  COULD  LEAD  TO  AN  UNSAFE  SITUATION  BY
THE  ELT  PREVENTING  THE  TRANSMISSION  OF  THE
DISTRESS MESSAGE. ONCE INSTALLED IN THE MOUNTING
BRACKET,  THE  INSTALLER  MUST  BE  SURE  THAT  THE
TRANSMITTER  IS  FIRMLY  ATTACHED IN  ITS  BRACKET  BY
TRYING TO EXTRACT IT MANUALLY, THEREBY VERIFYING
THERE  IS  NO  PLAY  AND  THAT  IT  REMAINS  ATTACHED
WHEN EXTRACTION FROM THE BRACKET IS ATTEMPTED.

(d) Connect connectors (4) to the unit.

(e) Carry out a first power up - 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).

WT9 Dynamic LSA. AIRCRAFT MAINTENANCE MANUAL (AS-AMM-01-000, 22. 05. 2017) - page 15