maintenance schedulefor thel410 uvp-e20 aeroplanewithout overhaul

MAINTENANCE SCHEDULE FOR THE

L410 UVP-E20 AEROPLANE WITHOUT OVERHAUL

Chapter 9.7. is approved by the Civil Aviation Inspection of the Czech Republic in Prague

\37h August 1995

LET KUNOVICE 686 04 Kunovice Czech Republic

We cannot correct an error unless we know of its existence, therefore, it is essen- tial that you do your part. Comments, corrections regarding this manual are wel- comed and should be sent to:

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or fax us to:

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or send us e-mail to:

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I @ 1998 LET, a.s.. 686 04 Kunovice, Czech Republic

All rights reserved. No part of this manual may be reproduced or transmitted in any form or by any means, electronic or mechanical, including photocopying and recording, for any purpose without the express written.permission of LET, a.s..

. , I

LET L 410 UVP-E20

-1NTENANCE SCHEDULE

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Rev. No.

5 .

RECORD OF REVISIONS

Date of Issue of New Pages

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LET L 410 UVP-E20


CONTENTS

1. INTRODUCTION ,SAFETY PRECAUTIONS ................. 2. AIRWORTHINESS LIMITATION SECTION - TIME

LIMITS/MAINTENANCE CHECKS ........................ 3. ROUTINE MAINTENANCE .............................. 4. PERIODIC MAINTENANCE ............................. 5. INSPECTION OF AEROPLANE .......................... 6. SEASONAL MAINTENANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7. UNSCHEDULED MAINTENANCE .......................... 8. STORAGE OF AEROPLANE ............................. 9. SUPPLEMENTS ......................................

9.1. Lubrication plan ........................... 9.2. List of overhaul works after which it is

necessary to carry out weighing of aircraft,

levelling of aircraft and service test flight

9.3. Survey of operation and lubrication materials

9.5. List of sealed items . . . . . . . . . . . . . . . . . . . . . . . . 9.6. List of adjustable items whose adjustment

during service is prohibited . . . . . . . . . . . . . . . . 9.7. Operation of instruments and' major components

Page

1-1

9.9. Statistics and elaboration of operation

defects influencing the operational safety 9.9-1

9.10.Special airframe inspections . . . . . . . . . . . . . . . . . 9.10-1

9.11.Repair of common defects without the

manufacturer's consent . . . . . . . . . . . . . . . . . . . . . . 9.11-1

9.12.Replacement of details . . . . . . . . . . . . . . . . . . . . . . 9.12-1

1 10. APPENDIXES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10-1

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1 I N T R O D U C T I O N ,

S A F E T Y P R E C A U T I O N S

-

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MAINTENANCE S C H E D U L E

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1.1. Introduction

1.1.1. General

1.1.1.1. The Maintenance Schedule (MS) determines the volume and periodicity of executing the maintenance on the L 410UVP-E20 aeroplane its systems and completing products.

1.1.1.2. The Maintenance Schedule determines the following types of

maintenance

- routine maintenance (see section 3) - periodic maintenance (see section 4) - inspection of airplane (see section 5) - seasonal maintenance (see section 6) - unscheduled inspections (see section 7) - maintenance during storage (see section 8)

1.1.2. General maintenance instructions

Upon finishing the adjustment of individual major

components and/or systems, opening of internal

compartments, dismantling of assemblies, aggregates and

major components and parts of the aircraft and engine

control system as well as other systems because of their

repair or exchange, it is necessary to make sure that they

are fully capable to operate at maximum values of their

parameters. Further it is necessary to ensure that the

position of the controlled element corresponds with the

position of the controlling element and with the

technical specifications. The check of the function of the

flight controls must be done from both pilot's seats.

1.1.2.2. In every case of the routine repair of parts removed from

the aircraft, of the replacement of faulty component,

repair of electrical wiring in the aircraft or its

equipment attachment and avionics, the following should be

done : - Aug 31/95 Page 1-3

LET L 410 UVP-E20


a) a test shop check of the repaired component (check of

main technical parametres)

b) an onboard test of functional ability:

- of the repaired component fitted in place - of the whole system with repaired component fitted or the system whose wiring of equipment fixture has been

repaired

- of the systems interconnected with the system

containing the repaired component or the systems with

repairs to themselves.

1.1.2.3. When doing any type of technical servicing it is

necessary to remove every defect and failure which

developed during the flight or that was found during

maintenance. In cases where the removal of defect(s)

would demand too much work or special tools, jigs etc.,

it is necessary to subject the decision whether the

aircraft may fly to the Minimum equipment list.

1.1.2.4. The scheduled maintenance work of all types must be done

using the prescribed ground equipment, mechanical means,

marked tools and check and measuring instruments.

1.1.2.5. All work listed in this Maintenance Schedule, as well as

all supplementary work on aircraft must be done in

accordance with the work procedure charts of the

Maintenance Manual for the L 410 UVP-E20 aeroplane.

1.1.2.6. Maintenance must be done by engineering personnel

trained for the individual specializations, properly

acquainted with aircraft design, operational

regulations, safety regulations, this Maintenance

Schedule for the L 410 UVP-E20 aeroplane and the work

procedure charts for maintenance.

Page 1-4 Aug 31/95



The personnel is thus allowed to service (maintain) the

L 410 UVP-E20 aircraft according to the valid regulations

and is fully responsible for the completeness and quality

of all maintenance work.

1.1.2.7. All types of maintenance and work done on the aircraft

must be recorded in the technical documentation in

accordance with the valid regulations for the civil

aviation.

1.1.2.8. The scheduled work on the airframe, engines, propellers

and instruments is related to the number of flight

hours, number of landings or operation time (monthslyears).

The number of flight hours (operation time) is the period

recorded from the beginning of the take off to the stop

aircraft on runway after landing including all reverse

regimes.

1.1.2.9. Keeping record of flights with full wing-tip tanks.When

a take-off with full wing-tip tanks took place a record

into the aircraft log book,chapter V1,Aircraft

operational records,into the Remarks column,must be

entered, reading : "WTT + 'I.

1.1.3. Numberinq scheme of the Maintenance Schedule and

Cross-reference to Other Publications

The items of the Maintenance Schedule are numbered

identically with the numbering of the Maintenance Manual

of the aircraft, engine or propeller. The reference

numbers of the Maintenance Schedule items comprise an

additional letter, differentiating the operations on the

object of maintenance. For each reference number in the

Maintenance Schedule there is a work procedure chart of

the same number in the Maintenance Manual of the aircraft;

this gives a quick access to the necessary maintenance

information.

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PJlAINTENANCE SCHEDULE

1.1.3.2. List of Documents Related with this maintenance Schedule

Abbreviation used

in the text:

a) Maintenance Manual (MM) of the

L 410 UVP-E20 aeroplane Aircraft MM

b) Maintenance Manual of the

M 601 E or M 601 E-21 engine

c) Maintenance Manual of the

V-510 propeller

d) Flight Manual for the

L 410 WP-E20 aeroplane

e) List of Manufacturing,

operating and Repairing

tolerances of the

L 410 UVP-E20 aeroplane

f) Structural Repair Manual of

the L 410 aeroplane

g) Illustrated parts catalogue

for L 410 WP-E20 aeroplane

h) Check Flight Methodics for the

L 410 WP-E20 aeroplane

Engine MM

Propeller MM

Page 1-6 Jan 12/02



1.1.4. Revision

All revision in this Schedule are accomplished by the sheet

replacement. New sheets are sent to the holders (users) by

means of a Mandatory Bulletin.

New sheets are marked in the lower left corner with the date

of revision and the revised portion of the text is marked by

a vertical line on the left-hand side. When an unchanged

text is shifted to the next page this is not indicated. If

there is no amendment on the next sheet (except for the

shifting of text) the sheet is marked with a next date and

a letter "R".

Each revision is accompanied with a next llRecord of

revision^^^ (page 0-3). The holder ensures that date and

signature of person who entered the revision into given

volume is filled in.

In some cases a so-called "Record of Temporary revisions11 is

introduced, usually as an supplement to bulletin,

introducing the modification of aircraft, or for quicker

informing of the operator about a revision being prepared.

Record of Temporary revisions a temporary validity. Upon

issuing a new, revised sheet is the "Record of Temporary

revisions11 cancelled together with the original sheet. The

filing of listed in and cancelled "Record of Temporary

revision^^^ is made by the holder of the Maintenance Schedule

in the I1Record of Temporary revision^^^ (page 0-1).

1.1.5. Abbreviations

MM - Maintenance Manual - this abbre'viation is

uniform for all products despite differences of

wording in actual titles of their service

publications - see part. 1.1.3.2.

Jan 12/02 R Page 1-7



w/p - Work Procedure

LH - Left-Hand (Port)

RH - Right-Hand (Starboard)

Rud - Rudder

Elev - Elevator

MS - Maintenance Schedule

IELU - Integrated Electronic Limiter Unit

L/G - Landing Gear

n 4

- gas generator speed

n P

- propeller speed

V - indicated airspeed

Page 1-8 Jan 12/02 R

LETECKE ZAVODY a.s. L 410 W P - E 2 0


1.2. Safety precautions

1.2.1. Generally

1.2.1.1. Before doing checks and any work every safety precaution

must be carried out that prevents man-caused discharge of

static electricity, wilful switching-on of electric

devices, fire on board and human injury.

1.2.1.2. Ground electric power sources may be connected to the

aircraft on board electric system only with consent of

a specialist in charge of technical maintenance of given

aircraft. When connecting aircraft to the power supply,

during inspection and work it is mandatory to mark it

visibly with sign "AIRCRAFT ELECTRICITY ALIVEff.

1.2.1.3. During the refuelling must be all electric devices not

needed for the refuelling switched off and all assembly

and work stopped.

1.2.1.4. It is not permitted to disconnect cables and wiring,

remove covers from blocks change fuses and lamps on a live

equipment.

1.2.1.5. Before starting the engines make sure there are fire

extinguishers at hand, that wheels are chocked and that

there are no loose foreign objects in the vicinity of

aircraft.

Jan 12/02 R Page 1-9

LETECKE ZAVODY a - s . L 410 UVP-E20


1 . 2 . 1 . 6 . For t h e a c t u a l danger a r e a s around t h e a i r c r a f t w i t h

e n g i n e s runn ing see f o l l o w i n g drawing:

a ) w i t h e n g i n e s

a t i d l e power

b ) w i t h e n g i n e s

a t max. T/O power

1 . 2 . 1 . 7 . When i n s p e c t i n g t h e powerp lan t s a f t e r t h e i r shut t ing-down

it is n e c e s s a r y t o pay a t t e n t i o n t o h o t p a r t s of

e n g i n e ( s ) i n o r d e r t o p r e v e n t b u r n s caused by c o n t a c t w i t h

them.

1 . 2 . 1 . 8 . P o r t a b l e e l e c t r i c lamps, used d u r i n g t h e inspection of &h_e - - -

. . . . . . . . . . . . . . . . . . . . . .

a i r c r a f t , .must be w i t h o u t d e f e c t , must have p r o t e c t i v e

c a g e s and must n o t s p a r k when swi tched on; c o n n e c t i o n

c a b l e must have a r u b b e r o u t e r i n s u l a t i o n .

1 . 2 . 1 . 9 . A i r c r a f t max be s e r v i c e d t o wind speed of 1 5 m / s .

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LET L 410 W P - E 2 0


1.2.2. Safety principles for work on elevated surfaces

1.2.2.1. In order to prevent accidental slipping when working on

the wing, it is necessary to use footwear with soft-rubber

soles.

1.2.2.3. Work on elevated surfaces should be done wearing safety

harness (bel) with rope.

1.2.2.4. When wind blows more than 15 m/s, it is not permitted to

work on high ladders (higher than 1 m).

Safety principles for work on jacked-up aircraft

1.2.3.1. When jacking the aircraft up it is necessary to observe

the instructions given in Chapter 007 of the ~aintenance - - - - - -

Manual-of aircraft; - - - - - - - - - - - - - - - - - - - - - - -

1.2.3.2. When the aircraft is lifted-up on the jacks, it is

forbidden to start engines.

1.2.3.3. During lifting (lowering) of the aircraft no persons are

allowed under the aircraft, in the cockpit, passenger's

cabin or on the surface of the aircraft.

1.2.3.4. During the landing gear retraction test, when the aircraft

1.2.3.5. The aircraft may be lifted if the wind velocity does not

exceed 5 m/s.

1.2.3.6. Asymmetric lifting of the aircraft and asymmetric loading

of wing on jacked-up aircraft is not permitted.

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LET L 410 UVP-E20


Safety principles for work with electric equipment

1.2.4.1. When working on the aircraft it is forbidden to:

- leave the loose ends of wiring uninsulated, - leave open the panels of distribution devices and covers of connector boxes and devices which are under current.

1.2.5. Protection from Very Hiqh Frequencies

1.2.5.1. When checking equipment radiating very high frequencies it

is forbidden to get into the radiating field and make

refuelling the (also in the nearness of the airplane).

Safety principles for work with the B-3V synthetic oil

1.2.6.1. The B-3V oil is a toxic substance. When handling it

observe following rules:

- It is forbidden to eat, drink and smoke when handling

the B-3V oil. It is strictly prohibited to syphon oil

from one vessel to another by sucking it first into a

hose with one's mouth.

- All handling of oil must be done wearing special garment (protective overalls) and protective devices.

- Special working garment for handling the oil and the

protective devices should be stored in a reserved, set

aside locker (separated from normal personal apparel and

clothing).

If the special overalls or protective devices were

stained by the B-3V oil, it is necessary to replace the

overalls and thoroughly wash the protective devices with

warm water and soap.

- Page 1-12 Aug 31/95

LET L 410 UVP-E20


- Handling the oil system is permitted only after the

pressure to the level of atmospheric pressure and oil

temperature drops below +60°c. When pouring the hot oil

the worker must be standing on the windward.

- Persons handling the B-3V oil are to be sent for regular medical examination once a year. The initial medical

- - - - -

examination must be done i-mftediately - after - the worker

has been appointed to handle the B-3V oil.

- If the skin of the aircraft has been stained with the

B-3V oil, it is to be wiped clean with a piece of cloth

soaked in white spirit (petrol). The cloth must be

replaced after use.

1.2.7. Safety principles for work with oxyqen system equipment

1.2.7.1. To handle the oxygen system are allowed the persons who - - - - - -

passed the course- and have practica-l hands-on experience

with handling the oxygen apparatus.

1.2.7.2. oil, grease, dirt and carbon black (soot) must not come in

contact with parts of the oxygen equipment.

1.2.7.3. Ensure that pressure bottles and other parts of equipment

are not subject to hard knocks and other damage.

1.2.7.4. Do not exceed permitted pressures when filling the system;

ensure that firefighting equipment is ready before - - - - - beginning -of _the- fillin-g, - - -

- - - - - - - - - - - - - - - - -

1.2.7.5. For handling the oxygen equipment use the chrome (or

nickel) plated tools. It is forbidden to use tools with

damaged plating.

- Aug 31/95 Page 1-13

LET L 410 UVP-E20


1.2.8. Safety principles for use of flammable liquids

1.2.8.1. When cleaning the aircraft with petrol and when doing work

where flammable liquids must be used (cementing of the

rubber parts or cleaning), it is necessary to strictly

observe following precautions:

- - - - - - - - - - - - - - - - - - -

- - - - - - - - - - - -

The aircraft must -be -grounded electrically.

It is prohibited to smoke or to handle open fire within

10 metres from the aircraft.

Ensure that firefighting equipment is at hand.

If the handling of flammable liquids takes place in a

hangar, sufficient ventilation must be ensured, the

aircraft must stand on its wheels and there must not be

any obstacle or foreign objects at the hangar doors,

that would pprevent a rapid pushing of the aircraft out

of the hangar should such a necessity occur.

On-board batteries and ground power source must be . . . . . . . . . . . . . . . . . . . . . disconnected.- - - - - - - - - - - - - - - - -

No other work on the aircraft may be done.

Electric vacuum-cleaners, electric drills etc. must not

be used simultaneously with cleaning.

Portable lamps used must be of the explosion-proof type.

Workers handling flammable liquids must wear antistatic

footwear and they must not wear overalls made of

synthetic fibres (danger of static electricity's

dischaarge).

No brushes and clothes made of synthetic fibres may be

used for cleaning.

The supply o f flamgab_le liquid f-or cleaning m u s t not - - - - - - - - - - - - - - -

exceed 1 litre. If greater amount of the liquid is

needed, then it must be stored in closed metal vessels,

placed at lkast 10 metres from the aircraft.

Aug 31/95

LET L 410 UVP-E2O


2

AIRWORTHINESS LIMITATION

- - - - - - - - - - - - SE<3TION - - - - TIME - - - - - - - ~

LIMITS/MAINTENANCE CHECKS

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- Page 2 -2


Aug 31/95

LET L 410 UVP-E20


2.1. General

The service life of the airframe parts and airframe systems except the parts noticed in item 2.2. is 20000 flight hours or 20000 flight cycles.

2.2. List of airframe parts and systems liable to compulsory

replacements

Table of service life of the airframe and its systems

Ser , No.

Name

Rear landing gear 1) spar

Left rear cable 2)

Right rear cable 2

Central right cable

2 1

Central left cable

2 1

Front cable 2 )

Marking

May 15/98

Service Life ( LB 1

13 000 flight cycles

6 200 hr

6 200 hr

6 200 hr

Page 2-3

LET L 410 WP-E20

PJLAINTENANCE SCHEDULE

Ser . No.

Name

Aileron fabric skin

Aileron fabric skin

Elevator fabric skin

Elevator fabric skin

Fabric skins of rudder

Notes to the table:

Marking Service Life

B 025 641 P ribs No. 3-14

B 025 641 L ribs No. 3-14

B 533 201 P ribs No. 3-17

B 533 201 L ribs No. 3-17

B 531 201 N ribs No. 3-17

Fabric skin service life on condition

1) Valid up to the Serial No. 1817. Service life of the rear landing gear spar is increased to 20 000 flight cycles after carrging out Mandatory Bulletin No. L 410 WP-E/019a.

From Serial No. 1818 the service life is 20 000 flight cycles.

2) Elevator trim tab control cables.

Note to the Fiq.2-1:

Wing service life vs. percentage of take-offs with WTT full of fuel is shown on Fig. 2-1. Landing with full wing tip tanks is permissible only in case of emergency. In the event of extreme utilization of the airplane for take-offs with full wing tip tanks the airplane manufacturer will set a corresponding wing service life and modify the system of inspections.

Page 2-4 Jul 15/99

LET L 410 UVP-E20


- May 15/98 Page 2-5

LET L 410 UVP-E20

M-AINTENANCE SCHEDULE

I - ) Page 2-6


Aug 31/95

LET L 410 WP-E20


Aug 31/95 Page 3-1

LET L 410 WP-E2O


Intentionally left blank.

, Page 3-2

LET L 410 UVP-E20


3.1. General

The routine maintenance consists of:

- routine maintenance A - done before every flight unless stated in the remark with the given operation otherwise

- during immediately f 01 lowing flights (training flights) perform when airplane is filled with fuel

- routine maintenance B - done after every landing and in case of handing over the airplane for parking

- during immediately following flights (training flights) perform when airplane is filled with fuel

- routine maintenance C - done once a day after concluding the flight day or before the first flight after an interval between flights from 1 to 15 days. This maintenance has validity 24 + 12 hours.

The routine maintenance type A and B is allowed to be done by a pilot on condition that he was trained for this work and approved by the manufacturer or else organization having the certification for L 410 WP-E20 aircraft type checks. In case any defect occurs during the routine maintenance A and B which is done by the pilot, then these repaired only by a trained engineer.

defects shall be

Reference No. Scheduled Maintenance Check

Remove the blocking devices blindings and mooring (i.e. covers aileron security clamp propeller rudder and elevator blockings covers of engine air-inlet,starting generator air inlet, exhausts, Pitot mazzle and ventilation of toilet; blind flanges for static pressure pickups, wheel chock, earthing equipment blocking strut of stearing column, tether ropes)

Note

At temperatures of ambient air below - 2 0 ' ~ (when warming-up of engines with air is as sumed) remove the sheets from engines only after heating-up the engines with warm air.

- May 15/98 Page 3-3

Reference No.

Page 3-4

LET L 410 UVP-E20


Scheduled Maintenance Check

Carry out the exterior inspection

FIG 3-1 INSPECT THE EXTERIOR

Note

(A) - beginning of - - inspection ~

(1 1 Wingjsurface-, indications of fuel leakage, interceptors, rolling tabs; (2) Ailerons; (3) Intercep- tors, rolling tabs; (4) Wing flaps; (5) Engine covers, air ducts, propeller; (6) Main landing gear (working cylindre, lock, tyre, inflation of tyre as per compression; (7) Fuselage (skin, windows); (8) Tail surfaces; (9) Door of emergency exit; (10) Pilot's cockpit; (11) Nose landing gear (working cylinder, lock, tyre, inflation of tyre as per compression,; (12) Door of emergency exit (in case there is the door on the airplane).

- - - - - - - - - - - - - - - - - - - - ~~~~

May 15/98

Reference No.

012.00.00.G (valid for airplanes with emergency door in pilot's cockpit and passenger cabin)

LET L 410 UVP-E20



Remove and store the airsteps. Close and lock the main door.

Remove the blocking bolts from the emergency exits and put them into the pocket on the right side of the pilot's cockpit.

Refuel the airplane according to the assumed flight. The engineer or the pilot are responsible for proper closing of the fuel tank in case they make A or B maintenance type.

Defecate the fuel tanks (15 minutes after refuelling)

Defecate the fuel cleaners

Clear away the snow, ice and impurities from the surface of the airplane, slots and season gaps, serials.

Note

After the embar- king of passengers.

Vith airplanes having rubber fuel tanks older than 5 year (from the date ~f manufacture) zarry out a =heck as per item 028.00.00.C

3nly before the first flight.

3nly in winter ;eason.

Jul 15/99 Page 3-5

Reference No.

Page 3-6




Warm-up the cabin and the landing gear with hot air. Before starting the engines warm them up with hot air.

Install the storage battery.

Check-the voltage of every battery separately.

Connect the ground power unit.

Disconnect the ground power unit from the airplane.

Check the fixing of the load (baggage) and locking of spaces.

Check the pressure in the engine fire extinguishers.

~ ~

Check the pressure in the T 7607 (Dwg.No. B 594 280 N) extinguishers in the forward baggage compartment.

Note

4t low temperatu res below/about -20'~ on ground darm up the zabin always before take off. At temperatures about -20'~ uarm up cabin mly if need be. Preheating of engines with warm air perform at temperatures below -20'~ on the ground before take-off.

Only if removed.

After starting the engine.

Jan 12/02

Reference No.

J u l 15/99

LET L 410 WP-E20



Check the function of pilotage system.

Check the air pressure in the pneumatic system. - - - - - - - - - - - - - - - - - - - - -

Note

Check or set the correct time on thelDo once in aircraft clock. With mechanical clock wind i~ up.

Check the operation of the BUR-1-2G flight recorder.

Switch on the flight recorder for preheating.

Check the tyre inflation from the flattening of tyres.

- - - - - - - - - - - - - - - - -

- - -

Mount the storage battery (e.g. 21 NiCd 450-1).

Check the laminated cover of the antenna of weather (for soiling and damage).

Check the operation of the weather radar.

- - - - - - - - - - - - - - - - - - - - -

Check with pressure gauges the pressure in oxygen cylinders of instruments.

2 days.

Carry out only if mounted on the aircraft.

O n l y if removed;

Only in case when it is mounted on the aircraft under pre- reguisite of flight when using the weather radar.

cary -out only in mounted on the aircraft.

Reference No.

076.10.00.1 (Engine MM, technologic process 76.10.00.f)

Page 3-8

LET L 410 UVP-E2O



Close the screens of the side cover, space of the aircraft radio station on the right side of the front part of the fuselage and the screens of the side cover of the electric equipment on the left side of the front part of the fuselage.

Close the screens of the lower tilting cover of the engine nacelles.

Readjust the levers of the flap control behind the oil cooler in the engine nacelles.

Check whether the seal of setting maximum contingency rating has not been damaged.

Adjust the switches of the automatic feathering on engines.

Note

Carry out at a temperature of the ambient temperature below +20°c. Open the) screens with the rise of temperature above +20°c

Carry out at a temperature drop of the ambient air below -25O~. Open the screens with the temperature rise above -25O~.

Carry out at a temperature drop of the ambient air below +30°c and with the temperature rise above +30°c.

Carry out at temperature of ambient air below +20°c and with the temperature rise above +20°c.

LET L 410 WP-E20



Mount the screens on to the 443 512 506 705 oil coolers in the engine nacelles.

Disconnect the 4 4 3 512 506 705 oil coolers in the engine nacelles.

Discharge the rest of water from the system of water injection and make the inner preservation of the water injection system.

Fill the tank of the water injection system with water.

Note

Carry out at a temperature d r o ~ of ambient air below -5Oc. Dismantle with the temperature rise above ~ O C .

Carry out at a temperature d r o ~ of the ambient air below -40'~ Connect the oil coolers with a temperature rise above -25O~.

Carry out at a temperature d r o ~ of the ambient air below +loOc. Clear away the preservation of the water in jec- tion system witk the temperature rise above +20°c and check the operation of the system.

Carry out according to t h ~ requirement of the screw. Discharge water from the system at a temperature of the ambient air below +loOc.

Page 3-9

LET L 410 W P - E 2 0

MZLINTENANCE SCHEDULE

MAINTENANCE B

Reference No.

1 Page 3-10


Set the stops under the aircraft wheels.

- ~ - ~ ~ ~

Set the cover on -the Pitot tube and the sensors of the static pressure, the inlet openings to engines and generators and if need be also the covers on to the windshield and windows of the pilot's cockpit.

Secure the aircraft control by means of a blocking strut.

. Adjust the following devices on the aircraft : - blocking of propeller - blocking of ailerons - blocking of elevator - blocking of rudder - covers of air inlet to engines and generator

- covers of exhausts - covers on Pitot tube and blindings of sensors of static pressure

- cover of air inlet to the toilet.

?round the airpLane wi-th the- - ~ ~ ~ ~

grounding cable. J

Note

2arry out only in case of showing, raining, dust storm and in Zase if the sircraf t stoppage till the next flight isassumed to De more than 2 hours.

Carry out only in case when the stoppage time of the

' airplane till the next take-of f will exceed 2 hours.

Aug 31/95

Reference No.

May 15/98

012.00.00.G (valid for aircraft with emergency door i-n the - - - -

cockpit and the passenger compartment )

LET L 410 UVP-E2O



Anchor the aircraft - only in case that a wind having wind gusts exceeding 20 m/s (72 km/h) is anticipated.

Take over the aeroplane from the crew.

Take over the report on the technical state of the aircraft from the crew. Acquaint yourselves with the records in the deck diary concerning the defects of the aircraft sy-stems during - - - - - the flight.

- - - - - - - - -

Inspect the aircraft (among others cockpit windows, condition of passenger compartment and pilot's cockpit, condition of baggage compartment, toilet).

Open the entry door. Set the airsteps.

Inspect the control elements in the passenger cabin and pilot's cockpit. After concluding the works on the airplane remove the airsteps and put them inside the airplane. Close and lock the entry door,

- - - - - - - - -

Note

'arry out only in case if the stoppage time of 3ircraft till the next take-of f is mticipated to zxceed -2 - hour s . -

3nly in case $hen the stoppage time 2f the aircraft till the next flight will sxceed 2 hours.

Do after the stop of engines.

Carry out only in case when the stoppage time on the aircraft till the next flight will exceed - 2 hours

Page 3-11

Reference No.

D12.00.00. J (in effect for air- =raft with lmergency fioor in zockpit )

Page 3-12

LET L 410 UVP-E20


Scheduled Maintenance Check Note

Inspect the control elements in the pilot's cockpit: - control lever of landing gear - levels FUEL - parking brake

After concluding the works on the 3ircraft remove the airsteps and put it inside the aircraft. Close and lock the entry door. Close the door 2f the emergency exit and secure it inside by turning the bar. Check the seal of the emergency exit.

Zheck the disconnection of switches 2nd circuit breakers in the pilot's zockpit.

Remove the deck batteries in order to store them.

Carry out only in case when the stoppage time of the aircraft till the next flight will exceed 2 hours.

Carry out only in case of the aircraft stoppage for more than 12 hours and a temperature of ambient air below -25O~.

Aug 31/98

LET L 410 UVP-E20

M.AINTENANCE SCHEDULE

I

Scheduled Maintenance Check Reference

No.

025.00.00.B

026.20.00.C

029.12.00.A

032.40.01.G

033.50.03.A

1035.30.02.8

Check the completeness of emergency means (life-jacket, axe, first-aid kit, safety rafts, emergency supplies).

J u l 15/99

Inspect the sealing of guards of the push-button EXTINGUISHING.

Inspect the hand valves for the emergency control of the landing gear and the LUN 6577-8 wing flaps. Check their sealing.

Check the detector of the brake temperature of the main landing gear.

Remove the storage batteries from the aircraft (e.g. 21 NiCd 450-1) in order to recharge them in the charging station.

Clean and disinfect the moulds of the oxygen masks.

Note

Do only in case that the stoppage of the airplane till the next flight uill exceed 2 hours.

Zarry out in zase of the stoppage for more than 10 days.

Jary out as 3er crew s requirement.

Page 3-13

LETECKE ZAVODY a.s. L 4 1 0 WP-E20


MAINTENANCE C

Reference No.

Page 3-14


Inspect the inlet opening of air conditioning.

Check the operation of transducers 36 V.

Check the operation of both transducers 115 V.

Check the pilot's seats and the seats for passengers.

Inspect the net of polyamide.

Check whether there is no indication of fuel leakage on the lower wing surface.

Inspect the exit of vent tubes of the fuel tank.

Check visually leakege of the 443 958 219 001 through-flow heater of fuel.

Inspect the piping accessible without dismantling the covers as well as the hoses and instruments of the hydraulic system: - on the engine up to the fire wall - in the bay of the front landing gear

- in the nacelles of the main landing gear.

Note

Only with aircraft of carge version.

Jan 12/02

Reference No.

Aug 31/95

LET L 410 UVP-E20



Check the amount of hydraulic liquid in the main tank.

Check whether there is enough hydraulic liquid in the emergency hydraulic tank.

Inspect the static indicator SI(7).

Check the operation of the heating of the SI (7) static indicator.

Check the compression of shock absorbers of the leg of the main landing gear.

Inspect the shock absorbers of the landing gear, clean the piston rods of absorbers.

Inspect at accessible places the main landing gear, working cylinders, locks and the guides of mechanical indicators of the main landing gear.

Check the compression of the leg absorber of the front landing gear.

Inspect the absorber of the leg of the front landing gear. Clean the piston rod of the absorber.

Inspect the cylinder of the servo control of the front landing gear.

Note

Page 3-15

Reference No.

061.10.00.C (MM - propeller)

1 Page 3-16

LET L 410 UVP-E2O



Inspect at accessible places the front landing gear, the working cylinder and the mechanical lock.

Check the wear of lining and the working clearances. Inspect the brake cylinders and their piping.

Check whether all bulbs of signalling are on.

Inspect the check their

position lights operation.

and

Inspect the flash beacons and check their operation.

Check the sensors of the system of the overall and static pressure.

Check the comparison of values of the barometric and coding altimeter with the barometric pressure in the parking area of the aircraft.

Check the operation of signalling of the stalling. Inspect the terminal switch.

Check the position of the shifting carrier ring.

Note

Aug 31/95

Reference No.

361.10.00.G c m - - - - propeller)

373.11.00.A (MM - ongine 73.11.00.a)

079.20.00.B T M M - - - - ~

engine 79.20.00.a)

079.30.00.B (engine MM W/P 79.50.00.d)



--


Inspect the transfer rings.

Zlean and treat the propeller nrface.- - - -

- - - - - - - - - -

Inspect the agregates and pipings ~f the fuel system below the engine zowlings and the inlet channel.

:heck whether the seal of the maximum contingency rating ~f engine has not been damaged.

Inspect the instruments and pipings 3f - the oil syst-em. - - - - - - - - - -

Check the oil amount in the tank by means of the signalling of the minimum oil amount.

Inspect the 8 LUN 7377-8 valves in the left side of engine nacelles.

Note

Jan 12/02 Page 3-17

Reference No.

Page 3-18

LET L 410 WP-E20




Note

Aug 31/95

LET L 410 UVP-E20


P E R I O D I C

Aug 31/95

4 M A I N T E N A N C E

Page 4-1

LET L 410 UVP-E20



) Page 4-2 Aug 31/95

LET L 410 UVP-E20


4.1. General

4.1.1. The periodic maintenance consists of:

- line check 1 - is done periodically after every 10 + 1 days.

- check 2 - is done after every 300 + 30 flight hours.

- check 3 - is done after every 1 200 + 30 flight hours.

- check 4 - is done after every 2 400 + 30 flight hours.

Remark: - With some systems it is necessary to carry out the check also depending on the operation time (months) or on the number of landings. The time periodicity, or the number of landings is given in the column Note of the specified operation. The time works and works according to the number of landings may be done with the next lower periodical check. The checks according to periodicity have the tolerance + 15 days and for the checks done as per number of landings the tolerance is + 50 landings except for line check 1.

- The tolerances allow to delay check carrying out in the necessary cases but it does not allow adding tolerance ints interwal between checks.

- In case that another periodicity is given with the respective periodical check than stated with checks 1, 2, 3, 4, then a multiple of this check is given with the respective check defined always in the lower part of the page in a footnote (e.g. 2+ ........, to be done with every second check 2).

- During the checks after engine overhaul perform first check 2 after 300 + 100 flight hours.

Page 4 - 3

LET L 410 UVP-E20

Mi%INTENANCE SCHEDULE

4.1.2. The execution of maintenance works due to the number of

landings or calendar time does not relieve of the duty of

the execution of works according to flight hours.

4.1.3. Lubrication is done during overhauling of all types in

accdordance with the lubrication chart see supplement 9.1.

Cycle of periodical maintenance

The cycle of the periodical maintenance is counted:

- from the putting into operation of a new aircraft - from the last inspection of the aircraft.

- Page 4-4 Aug 31/95

LET L 410 UVP-E20


Name of Part/Unit Scheduled Maintenance Check

AIR CONDITIONING

Inspect the heating control flaps and their controls in the pilot's cockpit and passenger cabin. Check them for proper position.

Inspect the compensators in the air distribution ducting between the frames No. 8-9, 3-4 and 11-12. Replace the defective compensators.

Check the tightness of non- return valves and closing flap in the front cabin, passenger cabin, between the frames No. 2-3, wing, engine nacelles.

Check the function of the heating control flap on the left control panel. Lubricate the pull-ro#ds of the flap control. -

Carry out maintenance of the R 134 A Air conditioning system according to work procedures mentioned in of the L-410 UVP-E20 Maintenance Manual.

Chapter FI

Frequency Note

Only in case mounted in the aircraft.

Jul 15/99 Page 4-5

Reference No.

LET L 410 UVP-E2O


- --- - - -



Page 4-6

Frequency Note

Aug 31/95

Reference No.



- -- - - - -


AUTO FLIGHT

Remove the KS 272 A elevator trim tab servo,the KSA 372 X servos of aileron,elevator and rudder f r ~ m the aircraft and- check:

- evidence of corrosion or impurities in the area of the engage solenoid

- adjustment of the

- rope drive

After testing mount into the aircraft.

torque.

it again

Frequency Note

After 12 months at least. Only in - -

case mounted in the aircraft.

Chapter b1 Jan 12/02 Page 4-7

LET L 410 UVP-E20


Reference No.


Page 4-8

- - - - - - - - - . - - ~~~-~~


Frequency Note

Chapter

Aug 31/95

Reference No.

023.60.00.A

023.60.00.B

023.60.00.C

023.70.00.A

I

Jan 12/02




ZOMMUNICATIONS

Zheck the function of the shock absorbers of the rear panel in the pilot's cockpit.

Check the antenna (e.g. 5 QK 405 16)

Check the correct connection of the cable to the aerials VSW (e.g. 5 QK 405 16).

Check the static discharger.

Remove the static dischargers, clean their seating areas and mount them again back.

Examine all by-passes of moving parts. Check the realiability of their fixations.

Replace battery in the DK 120 Underwater acoustic beacon according to instruction on the label.

Frequency Note

After 12 months at least. Only in case mounted in the aircraft.

Chapter FI Page 4-9

Reference No.

LET L 410 WP-E20

MJLINTENANCE SCHEDULE



Frequency Note

Chapter F] Page 4-10 Aug 31/95

Reference No.


M-AINTENANCE S C H E D U L E

- - - - - - - - - - - -


ELECTRICAL POWER

Check the electric equipment in the power centre in the cabin ceiling between the 7th and 9th frame (accessible - -

after removing the lining) and in the front part of the fuselage between the 1st and 2 nd frame to the left and between the 2nd and 4 th frame to the right.

Examine (after disconnecting) the following connections:

- v1, v2, v3, v4, v9, v10, V19, V20, V25, V26, (in the transition fuselage-wing)

- V5, V6, V7, V8, V11, V12, -V15, -V1-6, V225, V226, ( in - the transition wing-engine)

- V33, V34, V227, V228, (in the transition engine-tank)

- V14, V212, transition

(on 26th

Check the condition of negative terminals:

- V94, V93 (condition of the negative poLe of -the gene-- rator with the frame on the right and left engine)

Frequency Note

3t latest after 48 months

Chapter 10241 Jan 12/02 Page 4-11

Reference No.

Page 4-12


M2XINTENANCE SCHEDULE


- V211-1,2 (connection of the negative pole of the desk battery with the frame under the floor of the right pilot)

- V73-1 (connection of the negative pole of the socket of the outer source with the frame).

Examine the parts of the electric equipment behind the fire walls of the engine nacelles (between the 8th and the 10th rib).

Inspect the cable system (connection plug-socket) without dismantling and the terminal boxes in the fuselage.

Check the operation of all circuit breakers not operating as switches in spaces between the 1st and 2nd frame, the 7th and 9th and after the 21st frame.

Check the automatic switching of inverters 36 V.

Check the automatic switching of inverters 115 V.

Checkt the fixing and measure the insulation resistances of the LUN 2102 or the LUN 2102.01 alternator.

Chapter 10241

Frequency Note

Jan 12/02

Reference No.

024.30.01.B (MM - Engine w/p 80.11.00.a)

024.30.01.C (Engine MM U/P 50.11.00.a)

Aug 31/98

LET L 410 UVP-E20

PJlAINTENANCE S C H E D U L E

N a m e of Part/Unit Scheduled Maintenance Check

Remove t h e LUN 2102 o r t h e LUN 2102.01 a l t e r n a t o r and hand it over t o t h e test room. After t e s t i n g mount it again on t h e a i r c r a f t .

Check t h e a l t e r n a t o r a t of t h e test room f o r :

- s e c u r i t y of attachment of t h e t o r s i o n ba r

- clean and inspec t t h e s t a t o r and r o t o r .

Inspect t h e a l t e r n a t o r .

Remove t h e LUN 2132.02-8 s t a r t e r -genera to r and hand over t o test room. Af ter t e s t i n g mount it again i n a i r c r a f t .

it

t h e

Check t h e brush length and t h e commutator on t h e LUN 2132.02-8 starter genera- t o r a t t h e test room.

Remove t h e LUN 2167.03-8 voltage regu la to r from t h e 3 i r c r a f t and hand it over t o the test room. Af ter t e s t i n g nount it again on t h e 3 i rcraf t .

-

Frequency Note

Page 4-13

Reference No.

LETECKE ZAVODY a.s. L 410 WP-E2O

M2kINTENANCE SCHEDULE


Chapter [=I Page 4-14

Check the function of the LUN 2167.03-8 voltage regulator at the test room. Inspect the regulator.

Inspect the contacts of the DMR-400 DSP differential relay.

Remove the storage batteries from the aircraft and give them to the recharging workshop. After testing and recharging mount them again on the airplane.

Recharge and inspect the batteries.

Examine the storage place for batteries between the 1st and 2nd partition.

Preserve the space of storage batteries.

Remove the LUN 2743.03-8 the LUN 2743.04-8 and hand it over to the test room. After testing mount it again in the aircraft.

Frequency Note

After 3 months at the latest.

After 3 months at

Jan 12/02

Reference No.

LET L 410 UVP-E20



With the volt-ammeter check at the test room: - basic inaccuracies - insulation resistance

Examine the SA 440/8 shunt.

Connect the external power source.

Disconnect the outer power source.

Inspect the socket of the SRAP 500 external power source.

Check the operation of the switch with the V 016 electromagnetic tripping.

Chapter /024/ Aug 31/98

Frequency Note

Do after finishing the inspection.

Page 4-15

LET L 410 UVP-E20



Reference No.

Frequency Name of Part/Unit Scheduled Maintenance Check Note

Chapter 1 0 2 4 1

Page 4-16 Aug 3 1 / 9 5

Reference No.

LETECKE ZAVODY ass. L 410 UVP-E20

-1NTENANCE SCHEDULE


EQUIPMENT, FURNISHINGS

Check the reliability of fixing of screw and passenger seats to the floor of the aircraft.

Inspect the navigator's table and its tilting mechanism.

Inspect the box with spare fuses.

Remove the DV-3 fan from the aircraft and hand it over to the test room. After testing mount it again in the aircraft.

Check the length of brushes of the DV-3 fan at the test room. Inspect the commutator.

Examine the frame door between the crew and passengers. Check its closing.

Inspect the structure of the nose and rear luggage compartment.

Frequency Note

Only on aircraft where the partion is installed.


Reference No.

LET L 410 UVP-E20



Inspect the fastening belts.

Inspect the cargo-related equipment.

Examine the emergency equipment (first-aid box).

Check the operation of push-buttons for calling the crew.

Replace battery in the ELT 10 or POINTER 3000 Emergency Locator Transmitter according to instructions on the label and in the following cases:

- after the transmitter has been used in an emergency situation

- after the transmitter has been operated for more one cumulative hour.

2heck the operation of ELT 10 3r POINTER 3000 Emergency Locator Transmitter.

Frequency

Only with airplanes of cargo type

The examination of the SP12 rescure rafts and the NAZ-7 emergency packet is done as per a separate documentation.


After 12 months: at least. Only in case mounted in the aircraft.

Chapter F1 Page 4-18 Aug 31/98

LET L 410 UVP-E20



FIRE PROTECTION

Check the correct operation of the fire signalling system of engines and the front baggage compartment by means of test push-buttons.

Remove the block of the BI-2A, power unit, 2nd series and hand it over to the test room. After testing mount it again in the aircraft.

Test the sensibility with the BI-2A power unit, 2nd series at the test room. Examine the power unit.

Remove the fire detectors (e.g. DPS) and hand them over to the test room. After testing mount them again in the aircraft.

Check the insulation resistance with fire detectors (e.g. DPS) on the test room. Examine the plugs of the detectors.

Inspect the DS-3 M2 smoke signalling.

Frequency -

Note

:heck also in the rear 3aggage zompartment in case :hat there is signalling installed.

Chapter FI Aug 31/95 Page 4-19

Reference No.


IXLAINTENANCE SCHEDULE


Exhange the DS-3 M2 signalling bulb. Check the operation of the smoke signalling by means of test push-buttons.

Replace the PP 3 pyrocartrid- ges .

Blow through the extinguisher piping with pressure air.

Check the pressure in the PPL (8) fire extinguishers of the engine.

Check the electric circuit of pyrocartidges.

Check the pressure in the FH 15-364 cabin fire extinguishers.

Inspect the cabin fire extinguishers FH 15-364 and check their weight.

Examine the thermal fuse.

Check the pressure in the L 410 6740-40 fire extinguisher in the rear baggage compartment.

Chapter bl Page 4-20

- --

Frequency Note

After 12 months at least.



3nly in case if mounted on the aircraft.

Jan 12/02

Reference No.

LETECKE ZAVODY a . s . L 410 UVP-E2O


Name of P a r t / U n i t Scheduled Maintenance Check

?LIGHT CONTROLS

Cnspect t h e by-passes on a l l noving p a r t s of t h e c o n t r o l s .

:heck a l l i n d i v i d u a l c o n t r o l z e n t r e s .

Inspec t t h e c o n t r o l c a b l e s a t 111 a c c e s s i b l e p l a c e s .

Ydjust t h e t e n s i o n of c a b l e s f o r t h e c o n t r o l of a i r e l o n s .

I n s p e c t t h e components made 3f e l e c t r o n f o r c o r r o s i o n .

2 + . ... do w i t h e v e r y second check 2

Chap te r 10271

Frequency Note

rhe a d j u s t - nent of t h e ;ens ion of :ables : o n t r o l l i n g the r u d d e r m d t r i m t a b s of t h e = l e v a t o r is lone w i t h the seasona l na in tenance - see ? a r t 6 .

4f ter 2 4 nonths a t l e a s t .

J a n 12/02 Page 4 - 2 1

Reference No.

Page 4-22

LETECKE ZAVODY a . s . L 410 WP-E20



Inspect the individual pull-rods and levers of the controls.

Inspect the threaded ends of the control pull-rods.

Check whether the lock nuts are not loosened on the pull-rods of the control of the trim tabs of the elevator, rudder and ailerons.

Inspect the dust arresters at the individual control parts.

Inspect rudder control cables at place frame N0.7 and No.26 with partial dismantling of control cables.

Check the clearance in the control of ailerons and trim tabs of ailerons.

Verify the operation of the electric control of trim tabs of ailerons.

Check the clearance in the control of the rudder and trim tabs of the rudder.

Chapter 10271

Frequency Note

After 24 months st least.

Jan 12/02

a

Q)

F; C

Id 4J

k

C 0

-d

c, Id

(3s

U a

)+'

F: rl -

d

Id a)

k

W

Id Q

) 0

Q

) C

4 c, A

U

Id

w c,

Q)

0 E

c, 4

.4

O

k

X

kc

,

U 4J

OC

Q)

C

OC

U

Uc

,

Reference No.

LET L 410 UVP-E20



Check the operation of push buttons of pushing the spoilers out.

Check the operation of the tabs of automatic rolling under the operation of engines.

Chapter (0271

Frequency Note

Page 4-24

LET L 410 UVP-E20

PJIAINTENANCE SCHEDULE

N a m e of Par t /Uni t Scheduled Maintenance Check

FUEL

In spec t whether t h e r e is no i n d i c a t i o n of f u e l leakage on the lower wing su r f ace i n the engine space before t h e Eire wa l l s .

"eck whether t h e r e is no f u e l leakage from t h e d r a i n tubes and d r a i n ho les of f u e l tanks .

Zheck t h e passage of t h e f u e l p ip ing .

In spec t t h e p ip ing and hoses ~f t h e f u e l system.

In spec t t h e rubber s l e e v e s u i t h f i l l i n g branches and t h e s c reens i n t h e f i l l i n g branches of f u e l t anks .

Chapter /0281

Frequency Note

Carry o u t w i t h a i r p l a n e s having rubber f u e l t anks o l d e r than 5 y e a r s .

A f t e r 4 8 months a t l e a s t . Hoses ope- r a t e d f o r more than 5 y e a r s must be v i s u a l l y i n spec t ed a f t e r e w y 300 f l i g h t - hours .

A f t e r 1 2 months a t l e a s t .

A u g 31/95 Page 4-25

Reference No.

LET L 410 UVP-E20



Check wing tip tanks condition.

When replacing the brushes remove the 410 PCR-1V (8), ECN-40 or LUN 6283-8 pump. After replacing the brushes it again on the aircraft and check the tightness.

Check the tightness of the pump in the aircraft. Check or replace the brushes, if need be. Inspect the commutator.

Replace the LUN 7691.01-8 inserts of fuel cleaners with new ones.

Check the operation of the 443 958 219 001 through-flow heater of fuel.

Check the adjustment of fuel gauges to the zero value, adjustment of signalling of the minimum fuel amount and with aircraft with tip tanks, check the operation of the level indicator.

2+ ... do with every second check 2.

Chapter /0281

Frequency Note

Only in case if mounted on the aircraft.

Do it after checking the fuel gauge as per item 028.40.01.B

May 15/98 Page 4-26

Reference No.

LET L 410 WP-E2O



Remove the LUN 1634.01-8 fuel gauge from the aircraft and hand it over to the test room. After testing mount it again in the aircraft.

Check the basic inaccuracies on the indicator of the LUN 1634.01-8 fuel gauge at the test room. Inspect the indicator.

Remove the indicator of the fuel gauge of the LUN 1674-8 end tank from the aircraft and hand it over to the test room. After testing mount it again in the aircraft.

When in the test room, check the basic inaccuracies on the indicator of LUN 1674-8 the fuel gauge. Inspect the indicator of the fuel gauge.

Remove the transmitter of the LUN 1649-8 fuel gauge of the end tank from the aircraft and hand it over to the test room. After testing mount it again in the aircraft .

At the test room check on the transmitter of the LUN 1649-8 fuel gauge: - basic inaccuracies - insulating resistance. Examine the transmitter of the fuel gauge.

Frequency Note

3nly with 2ircraf t uith end tanks.

Chapter /ozsl May 15/98 Page 4-27

Reference No.

LET L 410 W P - E 2 0



- - - --


Chapter /0281

Frequency Note

Page 4 -28 May 15/98 R

Reference No.

LET L 410 UVP-E20



HYDRAULIC POWER

Inspect the instruments, pipings and hoses of the hydraulic system. Check whether they are properly fixed after removing the following covers:

rear lower cover of the engine nacelle

upper transition cover fuselage-wing

side lining at the left side of the fuselage between the 8th and 14th frame

upper and front cover of the landing gear nacelle

covers at the side walls of the control panel

deck plates.

Inspect the instruments of the hydraulic system (accessible after the removal of covers of the working cylinders of the interceptor and rolling tabs).

Aug 31/95

Frequency Note

Hoses operated for more than 5 years must be visually inspected 3fter every 300 flight hours.

Page 4-29

Reference No.

I Page 4-30

LETECXE ZAVODY a.s . L 410 UVP-E20



Check the purity of the hydraulic liquid.

NOTE: In replacing AMG 10 hydraulic liquid with the AEROSHELL 41 or in

their mixing check the hydraulic cleaner inserts after 30,60,90 and 120 flight hours and watch the sediment on the cleaner inserts. In case black sediment appears on the cleaner inserts,clean the hydraulic liquid and replace the hydraulic cleaner inserts.

Inspect the hydraulic piping and hoses.

Deslime the main and emergency hydraulic tanks.

Remove the inserts of the LUN 7614.01-8 and 03-8 hydraulic purifiers and check them for purity. After mount the inserts again in the aircraft or replace inserts by new ones.

Check the inserts of the LUN 7614.01-8 and 03-8 hydraulic purifiers.

2+ .... do with every second check 2.

Chapter 10281

Frequency Note

see 029.00.00.D

To be done before the check of purity of the hydraulic liquid ( item 029.00.00. .I?).

Jan 12/02

LET L 410 UVP-E20



Check the pressure of technical nitrogen in the LUN 6953.02-8 and 05-8 hydraulic accumulators (main and braking system).

Remove the inserts of the LUN 7313.02-8 hydraulic cleaners and hand them over for cleaning. After cleaning mount them again in the aircraft.

Clean the inserts of the LUN 7613.02-8 hydraulic cleaners.

Check the operation of the emergency lowering of the landing gear, wing flaps and the operation of the emergency braking. Check the operation of the signalling "Lower the landing gearm. Check the correct operation of the mechanical indicators of the landing gear. Check the setting of the LUN 3159.01-7 limit switch.

Check the tightness of the overpressure system of the hydraulic system.

Chapter 10291

Frequency Note

May 15/98 Page 4-31

Reference No.


P.2AINTENANCE SCHEDULE


Inspect the colouring of the silicagel filling of the 3976 0872 air drier.

Replace the insert of the 723 900-4(8) cleaner.

Check the exit pressure of the LUN 6651.01-8 pressure reducing valve.

Check the operation of the LUN 7548-8 safety valve on the airplane.

Remove the thermal switches LUN 3192-8 from the aircraft and hand them over to the test room. After testing mount it again in the aircraft.

At the test room check on the LUN 3192-8 thermal switch: - permissible inaccuracies - insulation resistance. Inspect the thermal pick-up of the hydraulic system.

Remove the MA4 pressure gauge for testing it in the test room. After testing mount it again in the aircraft.

At the test room check on the pressure gauge the basic inaccuracies. Inspect the pressure gauge.

2+...do with every second check 1.

Frequency Note

Chapter FI 1 Page 4-32 Jan 12/02

LET L 410 WP-E20

PJlAINTENANCE SCHEDULE


ICE AND RAIN PROTECTION

Inspect the surface of de-icers .

Check the operation of the control box of de-icing.

Check the operation of the de-icing system of wings and tail surfaces.

Wash-up the rubber de-icers of wings and tail surfaces. Inspect the surface of de-icers. Renew the paint.

Check the condition of the compensator in the air distribution.

Inspect the condensate pit of the de-icing system of the airframe.

Check the free motion of the de-icing valve in the air inlet to the engine.

Check the opening of the by-pass flap in the lower tilting cover under the oil cooler.

Frequency Note


3nly in case when it is mounted on the aircraft.

Aug 31/95 Page 4 - 3 3

Reference No.

LET L 410 UVP-E2O

L v l A I N T E N A N C E SCHEDULE


Check the lenght of the strut in the retracted position on the MP 100 MT electro-mechanical strut. Inspect the strut.

Check the adjustment of 1-imit switches in- thg SKP 1( 8-) box of limit switches.

Remove the UK-1 or the UK-l(8) closing cock from the airplane and hand it over to the test room. After testing mount it again in the aircraft.

At the test room carry out on the UK-1 or the UK-l(8) closing cock: - cleaning - greasing of sliding surf aces. - - -

Inspect the stop vilve.

Check the operation of heating the Pitot tubes, sensors of the static pressure and sensor of the ram pressure.

Check the operation of the electric heating of the wind screen.

Check the correct operation of the TER-1M thermoregulators

Check whether the wiper is properly fixed and adjusted. If need be replace the rubber wiper.

Page 4-34

Frequency Note


Aug 31/95

Reference No.

LET L 410 WP-E20

MiAINTENANCE SCHEDULE


Chapter /030/ May 15/98

Inspect the protecting coat of wiper levers.

Check the operation of wipers.- - - - - - - - - -

Check the operation of de-icing of propellers in rest of engines.

Examine the LUN 7850 collector and its brushes.

Check the wear of carbon brushes of the LUN 7850 collector.

Examine the LUN- 1'771.3-8 and LUN 1771.4-8 signalling - - -

device of ice accre4tion. -

Check the operation of the signalling of ice amredtion.

Frequency Note

After 6 months 3t least.

Page 4-35

Reference No.

LET L 410 UVP-E20


Name of Part/Unit Frequency Scheduled ~aintenance Check Note

Chapter 1030 1 Page 4 - 3 6 May 1 5 / 9 8 R

Reference No.

LET L 410 UVP-E20



INSTRUMENTATION

Check the operation of the following electric instruments: - fuel gauge - temperature indicators in the cabin

- temperature indicators between the turbines

- landing gear indicators - flap indicators - LUN 1538.01-8 triplex indicator

- pressure gauges of the hydraulic system.

Inspect the instrument board, dampers of instrument board, hoses of the total and static pressure.

- - - - - - - - - - - -

Inspect the instruments onthe board, control panels and on the ceiling panel.

Inspect the blocks and the transmitters of the BUR-1-2G flight recorder and their fixing.

Check the operation of the flight recorder by means of the UVOP-1 device.

Frequency Note


Chapter 1 031 1 Aug 31/95 Page 4 - 3 7

Reference No.

LET L 410 UVP-E20

MJ%INTENANCE SCHEDULE


Check the operation of the flight recorder on the aircraft when switching-on by the limit switch on the landing gear leg with the starting of the engine.

Calibrate and record all ana- logous parameters and single commands and their decoding of the board recorder.

Check the dampers of the ZBN 1-1 recorder.

Check the driving belt of the feed mechanism of the MLP-23 tape of the ZBN 1-1 recorder.

Frequency Note

Only in case when mounted in the aircraft.

Only in case when mounted in the aircraft. After 12 months at least.

case when mounted in the aircraft.

Chapter F] Page 4-38 Aug 31/98

Reference No.

LETECKE ZAVODY a.s. L 410 WP-E20



3emove the 0,4 K LUN 1469.11-8 ?ressure switch from the 2ircraft and hand it over to the test room.After testing nount it again in the 3ircraf t.

Zheck on the 0,4 K LUN 1469.11-8 pressure switch 3t the test room: - operation (adjustment) - tightness.

Replace battery in the DK 120 Underwater acoustic beacon 3ccording to instruction on the label.

Chapter 10311

Frequency .... Only in case when mounted in the aircraft. After 12 months at least.

After 12 months at least. Only in case mounted in the aircraft .

Jan 12/02 Page 4-39

Reference No.

LET L 410 WP-E20




Frequency Note

Page 4-40 Aug 31/95

Reference No.

LET L 410 WP-E20



LANDING GEAR

Inspect the main and the nose landing gear. Examine the conductors on the landing gear legs and in the space of the main and nose landing gear.

Inspect at accessible places the conductors from limit switches on the locks of the main landing gear and on the cylinders of the main landing gear. Inspect all by-passes within the space of the main landing gear.

Inspect the legs of the main landing gear.

Inspect the split pins on the connecting bolts of the main landing gear leg.

............................. 2 + . . . do with every second

check 2.

Chapter 10321

Frequency Note

Yfter 300 landings at least.

I landings at t least.

Aug 31/95 Page 4-41

Reference No.

LET L 410 W P - E 2 0



Examine the smooth surface of the piston rod and the sealing of the main landing gear leg.

Examine the blindings (of 1 inen and metil ) of the main landing gear leg.

Check the pressure and the springing values of dampers of the main landing gear leg.

Preserve the surface of the lower hinged fixing at the main landing gear leg.

Check the clearance in the seat of the main landing gear.

- - - - - - - - - - - - -

2heck the tightening of the bushings of the mechanical indicators of the main landing gear leg.

------------------------------ 2+ . . . do with every second

check 2.

Frequency

4 Note

t After 600 landings at least.

After 300 landings at least.

After 1800 landings 3-t least .

After 300 landings 3t least.

Chapter 032/ ' Page 4-42 May 15/98

Reference No.

LET L 410 UVP-E20



Inspect at accessible places the conductors from the limit switch on the mechanical lock >f the nose landing gear and >n the cylinder of the nose landing gear. Inspect all ~y-passes within the space of the nose landing gear.

Inspect the locking of the bolt of the front landing gear leg.

Inspect the smooth surface of the piston rod of the nose landing gear leg.

Inspect the dusters on the slide valve of the servo drive and the piston rod of the damper of the nose landing gear.

Examine the blindings (of metal and fabric) of the nose landing gear leg.

Examine the damper and servo-drive of the nose landing gear leg.

Check the pressure and springing value of the damper of the nose landing gear leg.

Frequency Note


May 15/98

. Page 4-43

Reference No.

LET L 410 WP-E2O


Page 4 - 4 4


Check the clearance of the seat of the nose landing gear.

Check the reverse motion of the wheel of the nose landing gear to the neutral position. (To be done after the previous check according to item 032.20.00.L)

Check the clearance in the mechanical lock of the nose landing gear.

Remove the controller of the OP (8) landing gear and check the correctness of fixing of the lever extension, whether the nut fixing the switch to the body is not loosened, the correct operation of the trip. Inspect the controller of the landing gear and its surface finish. After inspection mount the controller again on the aircraft .

Check the pressure in the wheels of the nose and the landing gear. Check the wheel disks. Inspect the wheels and check the connecting bolts of wheels of the nose and the landing gear.

Inspect the tyres.

Frequency

+ 1 After 1800

at least.



Jul 15/99

LET L 410 UVP-E20

IXAINTENANCE SCHEDULE


Examine the toothed drive of the inert transmitter and its cables.

Check the operation of brakes (according to the pressure gauge of brakes).

Inspect the main wheels and brakes : - wheel disks completeness - wheel bearings - packing rings - brakes completenes Replace grease in bearings. Check the working clearance of brakes.

Remove the main wheels with brakes (for inspection). After inspection mount again on the airplane.

Frequency Note

At least after 12 months. (Grease in the bearings to be replaced after 300 landings at least) . This work must be carried out also with any exchange of the tyre .

After 24 months or 1 800 landings at least.

May 15/98 Page 4-45




Chapter

1 Page 4-46

Inspect the main wheels and rakes : - wheel disks complete. 3eplace the packing rings.

Examine the wheel of the nose gear : - wheel disk completeness - wheel bearings - packing rings. 3eplace grease in the ~earings .

3emove the wheel of the nose landing gear for inspecting. hfter checking and testing nount the wheel on the 3ircraft.

Inspect the wheel of the nose landing gear: - wheel disks completeness 3eplace the packing rings.

Frequency Note

After 24 months or 1800 landings at least.

After 12 months at least. (Replace grease in bearings after 300 landings at least) . Carry out this work also with every replacing - -

of tyre .

After 24 months or 1800 landings at least.

Jan 12/02

Reference No.

LET L 410 UVP-E20



Check the pressure of the technical nitrogen in the hydraulic accumulator of the LUN 6900-8 brakes.

Remove the LUN 1446.02-8 double pressure gauge from the aircraft and hand it over to the test room. After testing mount it again in the aircraft .

Check the permissible inaccuracies of the double pressure gauge at the test room.

Remove the MA-100 pressure gauge for testing at the test room. After testing mount it again in the aircraft.

Check the basic inaccuracies on the MA-100 pressure gauge at the test room. Inspect the pressure gauge.

Check the function of the inertial transmitters UA 27A-13 and UA 27A-14.

Frequency Note



I After 1 800 landings

+ at least.


Chapter /a32/ May 15/98 Page 4-47

Reference No.

LET L 410 UVP-E20



Check the signalling of switching-on the steering of the nose wheel (pedal and manual).

Preserve the inner space of the spring pull-rod of the motion control on ground.

Check the correct adjustment of the limit switch of the neutral position of foot control pedals and front wheel control.

Check the operation of the nose wheel control (pedal and manual ) .

Remove the BD (8) diode box from the aircraft and hand it over to the test room. After testing mount it again in the aircraft.

Check the operation of the BD (8) diode box at the test room. Inspect the diode box.

Remove the ZO-lS(8) delay circuit from the aircraft and handit over to the test room. After checking reinstall in the aircraft.

Check on the ZO-lS(8) delay circuit for delay time. Inspect the delay circuit.

Frequency Note

After 2 400 landings at least.


Chapter Fl Page 4-48 May 15/98 R

Reference No.

LET L 410 UVP-E20



LIGHTS

Check the function of the pilot's cabin lighting.

Remove the LUN 2412 instrument lighting power supply test and the LUN 2412.01 lighting control panel and hand them over to the test room. After testing mount them again on the aircraft.

Check the exit voltage of the LUN 2412 power supply test the LUN 2412.01 lighting control panel at the test room. Inspect the source and control panel.

Check the function of the passenger cabin lighting.

Check the front and rear baggage compartment lighting.

Check the operation of the lighting of the static indicator of ice-acreation.

t' Check the operation of the lighting of tail areas.

Check wing leading edge lighting for proper function.

Check the searchlights.

Frequency Note

Only in case when mounted or the aircraft.

Chapter 10331 Aug 31/95 Page 4-49

Reference No.

LET L 410 UVP-E20



Check the oparation of the emergency lighting (inner and outer) .

Examine fixing of storage batteries. Measure the voltage.

Chapter / 0 3 3 /

Frequency Note

Page 4-50 Aug 31/95

Reference No.




NAVIGATION

Check the operation and tightness of the system of the static and total pressure for instruments.

Blow the system of the static and total pressure when disconnecting the instruments of the total and static pressure.

Inspect the LUN 7750.01-8 of the system of the static and total pressure.

Remove the LUN 1113.x~-8 air-speed recorder from the aircraft and hand it over to the test room. After inspection mount it again in the aircraft.

Frequency Note


After connecting the instrument check the tightness of the system (as per 034. ll.OO.A).

The final figures xx concers only the execution of the scale.


Reference No.

LET L 410 UVP-E20



Check the permisseble inaccuracies on the LUN 1113.x~-8 air-speed recorder at the test room. Inspect it.

Remove the LUN 1140.x~-8 variometer from the aircraft and hand it over to the test room. After testing mount it again in the aircraft.

Checkt the following on the variometer at the test room: - permissible inaccuracies - airtightness of the static system.

Inspect the variometer.

Remove the LUN 1108.x~-8 air-speed recorder from the aircraft and hand it over to the test room. After testing mount it again in the aircraft .

Zheck the following on the 3ir speed recorder at the test room: - permissible inaccuracies - switching of signalling - permissible inaccuracies of the scale values.

Inspect the air-speed recor- ier .

Chapter 10341 Page 4-52

Frequency

The final figures xx

> concerns only the execution of the scale.

The final figures xx concerns only the execution of the scale.

May 15/98

Reference No.




Remove the LUN 1173.x~-8 air-speed signaller from the ~~ircraft and hand it over to the test room. After testing mount it again the aircraft.

Check the permissible inaccuracies of switching on the speed signalling device at the test room. Inspect the device.

Remove the LUN 1205.31-8 artificial horizon and hand it over to the test room. After testing mount it again in the aircraft .

Check on the LUN 1205.31-8 artificial horizon at the test room: - starting time - value of the steady current - inaccuracies of the scale data

- operation of break-down signalling

- operation of angle transmitters

- signalling of limit banking angle

- indication of slip - precession speed Inspect the artificial horizon.

Frequency --

Note

After 12 months at least. The final figures xx concerns only the execution of the scale.

Only when mounted in the

. aircraft.


Reference No.

034.22.02.C /MM-AGR-74 techno1 . process 034.22.00. *a)/

LET L 410 WP-E20

I?rZAINTENANCE SCHEDULE

- - - -


Check on the AGR-74-5 horizon 2nd series for: - operation of horizon inoperative signallization

- operation of hand symbol setting

Inspect the face of the horizon.

Remove the AGR-74-5 artificial horizon 2nd series from the aircraft and hand it over to the test room. After testing mount it again in the aircraft.

Check on the AGR-74-5 artificial horizon at the test room the following: - starting time - necessary current - operation of the push button - operation of the stabilizer of the failure of the artificial horizon

- transmitter signal - difference of voltage divi- der signal and transmitter

- rate of bank and longitudial incline

- inaccuracy of data on the tilting table.

Inspect the artificial horizon.

Chapter FI

Frequency Note


I Page 4-54 Aug 31/95

Reference No.

LET L 410 UVP-E2O



Remove the LUN 1215.x~ turn indicator and hand it over to the test room. After testing mount it again it the aircraft.

Check on the turn indicator at the test room: - permissible inaccuracies - outlet voltage - operation of the correction switch

Inspect the turn indicator.

Check the operation of the LUN 1221.01-8 liquid-type compass.

Compensate the LUN 1221.01-8 liquid-type compass.

Frequency Note

After 12 nonths at Least Further in zase of its nounting 3f ter reporting 2f faulty iata by the ;crew when finding ief ects luring ~verhaul .

Chapter 1 034 1 Aug 31/95 Page 4-55

Reference No.

LETECK~ ZAVODY a.s. L 410 WP-E20

J?XAINTENANCE SCHEDULE


Check the fixing of the antenna with the receiver for finding-out thunder storm fronts (e.g. RDS-81) and its state. Inspect inside the laminated cover of the antenna.

Measure the value of the contact resistance between the antenna with the receiver for finding-out thunder storm fronts and the frame of the aircraft.

Inspect the BENDIX/KING antennas. Measure the contact resistance between the antenna and the flange.

Check ATC transponder.

Check navigation system VOR/ILS/MKR.

Inspect the antenna of the LUN 3593.30-7 receiver for the glide path radio beacons. Measure the contact resistance between the antenna and the flange.

Check the LUN 3596-7 navigation antenna.Measure the contact resistance between the antenna and the flange.

Chapter F I Page 4-56

Frequency

4 Note


- 1 After 24 - 1 months least.

L Jan 12/02

Reference No.

LET L 4 1 0 WP-E2O

IYLAINTENANCE SCHEDULE


OXYGEN

Check the portable oxygen apparatus for the absence of impurities and for their proper fastening.

Inspect the oxygen masks and check its operation.

Frequency Note

3nly in case when installed in the aircraft.

Aug 31/95

Chapter / 0 3 5 1 Page 4-57

Reference No.

LET L 410 UVP-E20




Frequency Note

Page 4-58 Aug 31/95

Reference No.

LET L 410 WP-E20


- ppppp


WATER WASTE

Chapter j0381 Aug 31/95

Frequency Note

Page 4-59

Reference No.

LET L 410 UVP-E20



- - - - - - - - - - - -


Frequency Note

Page 4-60 Aug 31/95

Reference No.

LET L 410 WP-E2O



STANDART PRACTISES AND STRUCTURES-GENERAL

Inspect the skin of the aircraft .

Inspect the paint of the aircraft.

Inspect the legibility of inscriptions and operation symbols of the aircraft.

Check the tightening of screws of removable covers being a part of the bearing skin.

Inspect the draining openings of the airframe.

Chapter PI Aug 31/95

Frequency Note


After 24 months 3t leas$.

Page 4-61

LET L 410 WP-E2O

JXAINTENANCE SCHEDULE

Reference No.



Chapter F]

Frequency Note

Page 4-62 Aug 31/95

Reference No.

LET L 410 UVP-E2O



'heck the main and emergency loor and their suspensions. 'heck the reliability of locks. Grease the lock of the loor.

Xeck the door of the front Daggage room, the lock and strut. Grease the lock.

2heck the operation of signalling the closed door, loor of emergency exit, door 2f the rear baggage room and the locks of the front baggage room.

Zheck the guards of the main landing gear, pull rods of t h ~ guards of the landing gear. Zheck the adjustment of zlosing of the landing gear.

Chapter F]

--

Frequency Note

Aug 31/95 Page 4 - 6 3

Reference No.

LET L 410 WP-E20

PJLAINTENANCE SCHEDULE



Frequency Note

Page 4-64

Reference No.

LET L 410 UVP-E20



FUSELAGE

Examine the rubber parts of the fuselage.

Check the state of components made of laminated glass.

Inspect the room behind the 21st partition whether not soiled.

Check the area of the fixing of locks of the main and nose landing gear and of working cylinders.

Check the reliability of the fixing of instruments in the front part of the fuselage.

Check the lower flange of the landing gear beam at the 14th partition wall on the left and right side in the area of rivet holes.

Wash the inner spaces of the landing gear nacelles.

Inspect the landing gear nacelles.

.............................. 2+ . . . do with every second

check 2.

Chapter 10531 Aug 31/95

Frequency Note

ifter 24 nonths it least.

ifter 24 nonths it least.

Page 4-65

LET L 410 WP-E20

M2iINTENANCE SCHEDULE

Reference No.

Page 4-66


Check the floor in the pilot's cockpit.

Renew the paint of the rubber anti-ice-accreation bands on the fuselage.

Check the fuselage skin at the level of propeller rotation.

Check the skin area in the place of the stop for entry stairs.

Examine at accessible places the suspensions (connecting points ) "wing-f uselagel', "tail areas - fuselage".

Inspect the transition guards of the fuselage with the wing and tail areas.

Chapter Fl

Frequency Note

kf ter 6- aonths 3t least.

-

A u g 31/95

Reference No.

054

054.00.00.A

054.00.00.C

054.00.00.D

054.00.00.E

LET L 410 W P - E 2 0



NACELLES

Inspect the air channels.

Inspect the engine nacelles (frame and skin).

Check the packing flags, rubber parts and leather packing elements in the dividing planes of guards.

Check the setting of lever locks of engine guards.

2+ . . . do with every second check 2.

Frequency Note

Chapter 1 054 1 Aug 31/95 Page 4-67

LET L 410 UVP-E20




Frequency Note

Page 4-68 Aug 31/95

Reference I NO.

LET L 410 UVP-E20



STABILIZERS

Inspect the tail surface.

Inspect the elevator and rudder.

Inspect the edge bands on the tail surface.

Check whether there is no clearance in the suspensions of the elevator and rudder.

Inspect the skin of the stabilizer and the integrity of spot welds.

Check the reliability of the fixing of control drums of balance tabs of the elevator and of the web.

Inspect the elevator in the area of the fixing of the control lever.

Frequency Note

4f ter 3 months 3t least.

Chapter Fl Aug 31/95 Page 4-69

Reference No.

LET L 410 UVP-E20




Frequency Note

Page 4-70 Aug 31/95

Reference No.

LET L 410 UVP-E20



WINDOWS

Inspect the windscreen.

Inspect the windows of the passenger cabin.

Chapter 1056/

Frequency Note


Aug 31/95 Page 4-71

Reference No.

LET L 410 UVP-E20




Frequency Note

Page 4-72 A u g 3 1 / 9 5

Reference No.

LET L 410 WP-E20



Inspect the flange in the region not covered with skin.

Inspect the whole surface of the wing.

Examine the tapes and fabric blindings in the and moving surfaces wing shroud.

Inspect the linen skin of airelons. A B n S

Inspect the skin on the lower wing surface.

Inspect the suspensions of wing flaps and airelons at accessible places.

Inspect the lower fixing bolts connecting the rear wing suspension with lower flange.

Inspect the trailing edge of airelons and wing flaps.

Inspect the interceptors and rolling tabs.

Inspect the skin of wing flaps and slots.

Frequency Note


Chapter 10571 Jul 15/99 Page 4-73

Reference No.

Page 4-74

LET L 410 WP-E20


Name of ~art/Unit Scheduled Maintenance Check

Zheck the radial and axial zlearance of bearings of mo- ring areas and their proper securing.

Zheck the surface of leading sdges of wing flaps and slots in places where a contact may xcur between the wing flap ~ i t h the slat and between the slat and the trailing edge of the wing.

2heck the gap between the interceptors and the trailing zdge of the wing.

Inspect the rubber stops of interceptors and rolling tabs.

2+... do with every second check 2.

Frequency Note

9fter 24 nonths 3t least.

Aug 31/95

Reference 1 NO.

061.00.10.C (Prop. MM)

061.00.10.D (Prop. MM)

061.10.00.D (Prop. MM)

061.10.00.F (Prop. MM)

061.10.00.H (Prop. MM)

061.10.00.1 (Prop. MM)

061.10.00.J (Prop. MM)

061.20.01.A (Prop. MM)

LET L 410 UVP-E2O



PROPELLER

Inspect the propeller the propeller speed limiter, the electrohydraulic controller, auxiliary pump, pressure switch and collector.

Inspect the trasmission system of the feedback. Check the system of the compound coupling.

Inspect the clearance between the slide blocks and thrust ring.

Check the fixing of the front propeller cover.

Check the securing of the propeller.

Inspect the conductors.

Inspect the joints on the propeller.

Inspect the propeller cover.

Clean the LUN 7816 propeller speed governor.

Frequency Note

30 also 3f ter the first 10 30UrS.

Do also 3f ter the first 10 hours.

Do also 3f ter the first 10 hours.

Chapter 1061 1 A u g 31/95 Page 4-75

LET L 410 UVP-E20



Clean the LUN 7880.01-8 electro-hydraulic actuator.

Check the operation of the LUN 7840-8 auxiliary pump.

Remove the ZO-4s(8) retarding circuit from the aircraft and hand it over to the test room. After testing mount it again in the aircraft.

Check on the retarding circuit 20-4s-8 the retarding time. Inspect the retarding circuit.

Page 4-76

Chapter bi

Note

-

May 15/98

+

+

1 2 3 4

- + + +

- + + +

-

- - -

Frequency

-

LET L 410 UVP-E20

-1NTENANCE SCHEDULE

Reference No.


061.00.10.E (Prop. MM)

77.15.00.a (Engine MM page 505)

77.55.00.a (Engine MM)

77.56.00.a (Engine MM)

POWER PLANT

Check with engines running:

- operation of the startergenerator

- operation of the automatic switching of busbars

- voltage of startergenerators

- measure the voltage on the A-71-1 and the A-71-2

- operation of hydraulic pumps

- operation of the automatic blade feathering

- operation of the propeller speed limiter

- operation of the torque channel

- operation of the system of limiters IELU by means of the switch TEST

- operation of the LUN 5223 generator speed derivative element

2+... do with every second check 2.

Chapter F] Aug 31/98 Page 4-77

LET L 410 UVP-E20

-1NTENANCE SCHEDULE

Reference Name of Part/Unit No. Scheduled Maintenance Check

371.20.00.A Inspect the suspensions (connection centres) of the wing with the engine mount and the engine hinges.

Chapter /071/

Frequency Note

lo also sith every zhange of che engine.

Page 4-78 Aug 3 1 / 9 5

Reference No.

072.02.00.A (Engine MM W/P 72.02.00.a)

072.02.00.B (Engine MM W/P 72.02.00.b)

072.22.00.A (Engine MM W/P 72.22.00.a)

072.23.00.A (Engine MM

072.33.00.A (Engine MM W/P 72.33.00.a)

072.90.00.A (Engine MM W/P 79.10.00.c)

072.90.00.B (Engine MM W/P 79.10.00.b)

LET L 410 UVP-E20


Name of ~art/Unit Scheduled Maintenance Check

M 601 E OR M 601 E-21 ENGINE

Check visually the fixing of instruments of the fuel and oil installationstfixing of the startergenerator,alternator and ignition.

Inspect the electric system of engine instruments.

Inspect the air bulkhead.

Inspect the inlet screens of the engine.

Inspect the engine suspensions.

Inspect the magnetic plugs of the reducer,drive boxes and oil tank.

Replace the insert of the oil cleaner.

2+....do with every second check 2.

Frequency Note

30 the inspection 3f the plug ~f the box 2nd reducer slso in zase when the signal lamp chips goes on.

Chapter )0721 Page 4-79

(Engine MM W / P 79.50.00.a 79.50.00.c)

LET L 410 UVP-E2O


Frequency

Chapter 10721

Note

q i t h e v e r y l f t e r 300, 300 and L500 hou r s . 4 f t e r 1 2 nonths a t Least.

Aug 31/95 Page 4-80

Refe rence No.


W/P 73 .11.00.a)


LET L 410 WP-E2O


N a m e of Par t /Uni t Scheduled Maintenance Check

E N G I N E FUEL AND CONTROL

Inspec t t h e components and piping of engine f u e l system under t h e engine cowlings and t h e i n l e t chane l .

I n spec t and wash t h e main f u e l = l e a n e r s of t h e LUN 6290.04-8 f u e l pump.

2 + . . . do w i th every second check 2 .

Frequency Note

Aug 31/95 Page 4-81

Reference No.

LET L 410 UVP-E20




Chapter /073/ Page 4-82

Frequency Note

A u g 31/95

Reference No.

374.10.00.A (Engine MM ;J/P 30.21.00. page 501)

374.10.00.B (Engine MM ;J/P 30.22.00 page 401)

LET L 410 WP-E20



IGNITION

Check the ignition system on the aircraft by means of the testing device.

Replace the low-voltage spark plugs.

2+.. . do with every second check 2.

Chapter 1074 1

Frequency Note

Aug 31/98 Page 4-83

Reference No.

LET L 410 UVP-E2O




Page 4-84

Chapter 1074 /

Frequency Note

Aug 31/95

Reference No.

LET L 410 WP-E20

MA.INTENANCE SCHEDULE


Chapter (0761 J u l 15/99

ENGINE CONTROLS

Check the operation of control levers of engines - Dower control - propeller -control - closing of fuel valves on engine (closing valves of fuel )

- closing of the main fuel inlet (fire valves).

Check the necessary force at the lever and controlling the fuel closing valves.

Check the tension of the engine control cables in the vertical channel behind the cockpit. - - - -

- - - - -

Check the force at the power lever on the front control panel.

Check the adjustment of kine- matics motion of the engine controls.

.............................. 2+...do with the first check :

and then with every second check 2.

Frequency Note

Carry out also with any exchange of the engine.

Page 4-85

Reference No.

076.10.00.A (Engine MM W/P 76.10.00.b)

076.10.00.B (Engine MM- W/P 76.10.00.c)

076.10.00.C (Engine MM W/P 76.10.00.e)

076.10.00.D (Engine MM W/P 76.10.00.g)

076.10 .-00-. E (Engine MM W/P 76.10.00.h)

076.10.00.F (Engine MM W/P 76.10.00.a)

076.10.00.G (Engine MM W/P 76.10.00.d)

- - - - -

Page 4-86

LET L 410 WP-E2O



Check the clearance V 3 .

Check the motion of the - - - - - - " Bc If 1 ever.

Check and adjust the length of the push-pull rod.

Check the operation of the engine controls. Lubricate the spherical bearings and the feathering pick-up lever.

Wash dnd lubricate the automatic feathering switch lever.

Inspect the levers and pull rods of the engine control. Check the limit positions of the control levers of the engine.

Check the end positions of the control lever of the fuel closing cock.

2+....do with every second check 2.

Chapter 10761

Frequency Note

Reference No.

O76.lO.00 .E (Engine MM W/P 77.55.00.b)

LET L 410 UVP-E20



Check the operation of the limiter system under the operation of engines.

Remove the LUN 5260.04 or LUN 5260.05 integrated electronic limiter unit from the aircraft and hand it over to the test room. After testing mount it again in the aircraft .

Check on the LUN 5260.04 or the LUN 5260.05 the number of actions and amplifications of limiters, power consumption. Inspect the IELU.

Remove the LUN 5223 generator speed derivative element from the aircraft and hand it over to test room for testing. After testing mount it again in the aircraft.

Check on the LUN 5223 generator speed derivative element at the test room: - output voltage - operation. Inspect the generator speed Aerivative element.

Frequency Note

To be done if the a-c uas out of pera at ion 3t min. 10 days.

Chapter /0761 May 15/98 Page 4-87

Reference No.

376.15.00.A (Engine MM Y/P 77.15.00.a)

076.15.00.B (Engine MM W/P 76.30.00.a)

076.52.00.A (Engine MM W/P 77.52.00.a)

076.52.00.B (Engine MM W/P 76.30.00.a)



- -- - --


Remove the LUN 1476-8 torque limiter pressure switch and hand it over to the test room for testing. After testing mount it again in the aircraft.

Check on the LUN 1476-8 torque limiter pressure switch at the test room: - basic data - insulation resistance. Inspect the torque limiter pressure switch.

Check the adjustment of the LUN 7370-8 fuel valve control.

Remove the switch of the LUN 3280-8 automatic feathering pressure switch and hand it over to the test room for testing. After testing mount it again in the aircraft.

Check on the LUN 3280-8 automatic feathering pressure switch at the test room: - basic inaccuracies - insulation resistance. Inspect the switch.

Frequency Note

Chapter 10761 Page 4-88 Jan 12/02

LET L 410 UVP-E2O



ENGINE INDICATING

Remove the LUN 13 47. xx generator speed indicator from the aircraft and hand it over to the test room. After testing mount it again in the aircraft.

Check on the LUN 1347.x~ generator speed indicator the basic inaccuracies at the test room. Inspect the speed indicator.

Remove the LUN 1348.x~ propeller speed indicator from aircraft and hand it over to the test room. After testing mount it again in the aircraft .

Check on the LUN 1348.x~ propeller speed indicator the basic inaccuracies at the test room. Inspect the speed indicator.

Remove the LUN 1540.02-8 torque transmitter set and the LUN 1539.02-8 torque indicator and hand them over to the test room. After testing mount them again in the aircraft.

Frequency Note

?ha1 fi- jures zoncern only the zxecution 2f the ;cale.

Aug 31/95 Page 4 - 8 9

Reference No.

- -- - -- --

077.11.00.B (Engine MM W/P 77.11.00.a)

077.22.02.A (Engine MM W/P 77.22.00.b)

077.22.02.B (Engine MM W/P 77.22.00.a)

LET L 410 UVP-E20

L\?LAINTENANCE SCHEDULE


Check on the LUN 1540.02-8 torque transmitter set and on the LUN 1539.04-8 torque indicator set at the test room: - basic inaccuracies - insulating resistance Inspect the transmitter and the indicator.

Remove the LUN 1370.02-8 inter turbine temperature indicator from the aircraft and hand it over to the test room. After testing mount it again in the aircraft .

Check on the LUN 1370.02-8 inter turbine temperature indicator the basic inaccuracies at the test room. Inspect the thermometer.

Remove the LUN 1358-8 oil temperature transmitter from the aircraft and hand it over to the test room. After testing mount it again in the aircraft .

Check on the LUN 1358-8 oil temperature transmitter at the test room: - basic inaccuracies - insulating resistance. Inspect the temperature transmitter.

Frequency Note

Page 4-90 Aug 31 /95

Reference No.

078.10.00.A (Engine MM W/P 78.10.00.a)

LET L 410 WP-E20



EXHAUST

Inspect the exhaust bends.

Chapter F]

Frequency Note

Aug 31/95 Page 4 - 9 1

Reference No.

LET L 410 UVP-E20

m I N T E N A N C E SCHEDULE

-


- - -


Frequency Note

Page 4 - 9 2 A u g 31/95

Reference No.

079.30.00.A (Engine MM W/P 79.50.00.b)

079.40.00.A

LETECKE ZAVODY a.s. L 410 WP-E2O

PJZAINTENANCE SCHEDULE


Zheck the oil amount in the ~ i l tank by means of a gauge.

Carry out visual inspection ~f oil system hoses.

Inspect the 443 512 506 705 oil cooler.

Remove the TPV 1 (7) thermostatic and overpressure valve from the oil cooler and hand them over to the test room. After adjusting mount it again in the aircraft.

Check the adjustment of the TPV l(7) thermostatic and overpressure valve at the test room.

Frequency Note

Operations specified in the following item are to be carried out only for hoses of more than 5 years in operation.

Chapter b] Jan 12/02 Page 4-93

Reference No.

Page 4-94

LET L 410 UVP-E20




Frequency Note

Chapter 1079 1 Aug 31/95

Reference No.

LET L 410 UVP-E20

JXULINTENANCE SCHEDULE


STARTING

Check the cycling time of the LUN 2601.01-8 time relay.

Chapter j0801

Frequency N o t e

Aug 31/95 Page 4-95

Reference No.

LET L 4 1 0 W P - E 2 0



Chapter 10801

Page 4-96

Frequency

Aug 31/95




WATER INJECTION

Check the operation of the LUN 5155-8 water injection Pump

4 + .... carry out with every 4th check 1

Frequency Note

Do in case the pump was depreservec

Jan 12/02 Page 4-97

Reference No.

. LET L 410 UVP-E20




Frequency Note

) Page 4-98 Aug 31/95

LET L 410 UVP-E20

MJLINTENANCE SCHEDULE

5

I N S P E C T I O N O F AEROPLANE

Aug 31/95 Page 5-1

LET L 410 UVP-E20



Page 5-2 A u g 31/95

LETECKE zljVODY a.s. L 410 UVP-E20

MZiINTENANCE SCHEDULE

I 5.1. General

5.1.1. The purpose of the aircraft inspection is the evaluation

of the technical state of the airframe and its systems.

I 5.1.2. The inspection of the aircraft is done after 4 800 hours + 150 hours, at least after 10 years from the date of the ' - - - - - - I - - - - - - - - - - - - - - - - - - - - - - - - - - - -

airplane takeover by customer or from dateof t h e latest

I overhaul or from the previous inspection.

5.1.3. During the inspection also operations according to the

overhaul of the periodic maintenance must be carried out,

i.e. according to this maintenance schedule of the

L 410 UVP-E20 airplane.

I

I 1 5.1.4. Based on the results of the inspection, the necessary

I repairs must be carried out so that the required flight I

I I - - - - - - -

I - - - safety level i s secured as well-as the ability of the I

- - - - - - - - - - - - - - - - -

I aircraft to fly till the next inspection. I

I I

1 5.1.5. The airplane inspection is carried out according to an

approved program in the airplane manufacturer's factory,

or in a repar factory autorized by the airplane

manufactorer and airworthines autority to do so and given

the necessary documentation by the airplane manufactorer.

Sep 25/01 Page 5-3 I

I

LET L 410 UVP-E20


Page 5-4


Aug 31/95

LET L 410 UVP-E20


S E A S O N A L

6 M A I N T E N A N C E

A u g 31/95 Page 6-1

LET L 410 UVP-E2O



Page 6-2 Aug 3 1 / 9 5

LET L 410 UVP-E20


6.1. General

The seasonal maintenance (seasonal work) is carried out

according to temperature changes (decreasing or increasing)

in area of aircraft operation.

The preparation works for the seasonal maintenance are

carried out within the scope of the nearest periodic

maintenance. - - - - - -

FLIGHT CONTROLS

1 6.2. Works which must be carried out with temperature decrease

Adjust the tension of the control cables in the rudder and elevator trim tabs.

HYDRAULIC BOWER

Note Reference

No.

Bleed the hydraulic piping of the landing gear control system in the landing gear nacelles.


LIGHTS

Remove from the aircraft the storage battery (e.g. 21 NiCa 450-1) in order to check it at the shop inspection. After the checks, reinstall it in the aircraft.

~- - - - - - - - - - - - - - - - -

Check the maximum charging current on the storage battery (e.g. 21 NiCa 450-1) and recharge the storage battery.

May 15/98 Page 6-3

LET L 410 UVP-E20


Reference No.


NAVIGATION

Check the errors of the Rn 45 ambient air thermometer.

PROPELLERS

Check the cycle time of the LUN 2601-8 propeller time relay.

Note

16.3. Work which must be carried out with temperature increase

Page 6-4

FLIGHT CONTROLS

Adjust the tension of the control cables in the rudder and elevator trim tabs.

HYDRAULIC POWER

Bleed the hydraulic piping of the landing gear control system in the landing gear nacelles.

May 1 5 / 9 8

LET L 410 UVP-E20


6.4. Limitations of the operation (maintenace)

The limitation for the operation is given in the L410 WP-E20

I Maintenance Manual, section 012.

- May 15/98 Page 6-5

LET L 410 UVP-E20



I - I I Page 6-6

LET L 410 UVP-E2O


UNSCHEDULED

Aug 31/95 Page 7-1

LET L 410 UVP-E2O


Page 7-2


A u g 31/95

LET L 410 WP-E20

-1NTENANCE SCHEDULE

7 . 1 . Conditions for doins unscheduled inspections

7 . 1 . 1 . Work to be done after a hard landing. A landing is

considered hard when the g-load in the centre of gravity

exceeds 2 , 5 as well as in case of:

- landing on the nose wheel - landing with a great banking angle (more than lo0) - undershoot (landing short of the runway) - leaving runway

7 . 1 . 2 . Work to be done after a landing at higher - than - permisible - maximum landing weight.

7 . 1 . 3 . Work to be done after the aircraft flew throught storm

activity and after the lighting strike.

7 . 1 . 4 . Work to be done during unscheduled inspections is given in

the table-point 7 . 2 .

- Aug 31/95 Page 7-3

LETECKE ZAVODY a.s. L 4 1 0 WP-E2O


7.2. Work done at the unscheduled inspections

Para of the MS or section of the MM

Hard landing

Lighting strike, flight in the storm activity

Landing at weight higher than max. landing weight

NOTE: - @TO be done in case the brakes were used at maximum

weight (without using the reverse - pitch braking)

In case the landing weight exceeded the max.

permissible landing weight, record the actual weight

and nature of landing into the aircraft logbook and

into the nose and main LG certificates (if

supplied). - - - - - -

Page 7-4 Jan 1 2 / 0 2

LET L 410 UVP-E20


1 7.3. Works carried out after bird impact After bird impact carry out the check according to following

items :

~ 023.12.02.A; 030.10.00.A; 030.20.00.B; 030.42.03.A;

033.40.00.B; 033.40.05.A; 034.11.00.A; 034.12.00.A; - - - - -

0 3 4 . 4 1 ~ 0 0 . ~ : 034.-5O.OO-.A; 034-.53.84;A; 034-.53;05.-A:

051.00.00.A; 052.80.00.A; 053.00.00.B; 053.50.00.A;

054.00.00.A,C;055.00.OO.A; 056.10.00.B;057.30.0O.A;

061.00.10.A (Prop. MM ) ; 061.10.00.J (Prop. MM ) ;

072.22.00.A (Engine MM ) ; 072.23.00.A (Engine MM ) ;

079.40.01.A.

- May 15/98 Page 7-5

LET L 410 W - E 2 0



-

Page 7-6 May 1 5 / 9 8

LET L 410 UVP-E2O


STOFL%GE OF AEROPLANE

A u g 31/95 Page 8-1

LET L 410 UVP-E20



Page 8-2 Aug 31/95

LET L 410 UVP-E2O


8.1. General

8.1.1. After putting the aircraft out of operation for more than

15 days it is necessary to execute works connected with

the prepraration for the storage, during storing and when

putting the aircraft into operation.

8.1.2. The extent of work connected with the prepraration for the

storage depends on the planned storage time.

8.1.3. There are the following types of storage:

- for a time of 15 to 30 days - for a duration up to 3 months - for a duration more than 3 months (i.e. 6 months,

9 months, 12 months).

8.1.4. The aircraft must be stored provided with all blinds and

covers.

Work done durinq the preparation for storinq

8.2.1. Work carried out for storing the aircraft for a duration

of 15 to 30 days.

8.2.1.1. Carry out the work in the extent of the routine

maintenance B - only works given for the case that the

stoppage time of the aircraft till the next flight is

presumed to be more than 2 hours.

8.2.1.2. The metallic parts on wipers, all screw heads fixing the

covers, door handles and other motionless parts on the

outer surface of the aircraft without protection by a

varnish or with a damaged varnish must be preserved with

the KRNB or K-17 GOST 10877-76 preserving wax.

- Aug 31/95 Page 8-3

LET L 410 WP-E20

Mi3INTENANCE SCHEDULE

8.2.1.3. The metallic parts on control levers of wing flaps and

airelons jon which the paint has been damaged, the

springs of the quick-release locks on the forward

fuselage covers, the piston rods of the landing gear

shock absorbers and other movable parts in the landing

gear space to be coated with preserving oil. The

quick-release locks of covers must be tightened after

preserving.

8.2.1.4. Clean the landing gear and after drying preserve the

metallic parts of it which are not protected by the

paint (excepting the brake working surfaces

and shock-absorber piston rods) with preserving wax.

8.2.1.5. Cover the cockpit windows with the L 410.9516 cover.

8.2.1.6. If the water injection system of the engine has not been

preserved, preserve it according to the working

procedure 082.00.00.A.

8.2.1.7. The fuel tanks must be filled-up to the full amount

(this does not concern the tip tanks).

8.2.1.8. The fuel system must be filled up with fuel and the fuel

cock must be closed.

8.2.1.9. Remove the storage batteries from the aircraft (e.g.

20 NKBN-25,SAFT,VARTA and 21 NiCd 450-1) and store them.

Carry out the maintenance as follows:

- 20 NKBN-25,SAFT and VARTA storage battery according to instructions in the Maintenance manual of the

20 NKBN-25,SAFT and VARTA storage battery

- 21 NiCd 450-1 storage battery according to aircraft

MM, chapter 033.

-

Page 8-4 Aug 31/95

LET L 410 UVP-E20


8.2.1.10. Ensure that the wheels of the aircraft rest on a hard,

even surface and that the aircraft is not inclined to

one side only. Treat the tyre by SVITPREN warhish

against surface craks.

8.2.2. Work done for the storinq of the aircraft for a duration

of up to 3 months - - - - - - - - -

8.2.2.1. Carry out work according to items 8.2.1.1. to 8.2.1.10.

8.2.2.2 Preserve the propeller see propeller MM, section

061.00.00.)

8.2.2.3. Preserve the engines (see engine MM, section 72.03.00.)

8.2.3. Work done for the storinq of the aircraft for a duration

of more than 3 months

8.2.3 .l. Carry out work-aceording to $terns 8.2.2.

8.2.3.2. Do the outer preservation of engines by spraying oil

KONKOR 101. At the same time protect the electric

installation and the ignition system against the oil

penetration.

8.2.3.3. Wash out the main wheel and nose wheel bearings and

preserve them with the L CSN 657131 or

K-17 GOST 10 877-76 preserving grease.

- - - - - - - - - - - - - - - - - - - - - - - - -

8.3. Maintenance of the aircraft durinq storinq

8.3.1. Maintenance of aircraft after any 15 days of storinq

May 15/98 Page 8-5

LET L 410 UVP-E2O


8.3.1.1. Inspect the engines, silicagel of indicators and carry

out works which are given in the section 72.03.00 of the

para "After 15 days of storingt1 in the MM-engine. Turn

the propeller by 10 revolutions so that the blade

originally pointing upwards now points downwards after

the propeller has been secured.

8.3.1.2. Check visually the pressure in the tyres and LIG shock

absorbers.

8.3.1.3. Check whether there is no humidity under the covers. If

so, remove the covers, dry them of and check the

aircraft surface for corrosion.

8.3.2. Maintenance of the aircraft after any 30 davs of storinq

8.3.2.1. If the aircraft is stored under tropical and subtropical

conditions, clean the windshield with antiseptic means

I in order to prevent the formation of mildew

I (ethylalcohol).

I

I 8.4. Work done when puttinq the aircraft into operation after

I storinq

I 8.4.1. Work done after storinq the aircraft for a duration of 15 I I to 30 days

: 8.4.1.1. Remove the covers from the aircraft.

I I 8.4.1.2. Remove the preserving wax from the preserved outer

I surfaces and the landing gear by means of cleaning I I petrol. Take care that the friction surfaces are not I greased.

I Page 8-6 Aug 31/95



8.4.1.3. Install the charged (e.g. 20 NKBN-25, SAFT, VARTA and

21 NiCd 450-1) storage batteries.

8.4.1.4. Remove the preservation from the water injection

sys tem.

8,4.1.5. - - - - - - Carry out the maintenance of the aircraft in the extent - - - - - - - - - - - - - - -

of the periodic maintenance 1 and the lubrication

corresponding to the respective season.

8.4.2. Work done after storinq the aircraft for a duration up to

3 months.

I 8.4.2.1. Carry out work given in items'8.4.1.1. to 8.4.1.5.

8.4.2.2. Remove the preservation from engines (see engine MM,

section 72.03.00).

8- 4r2.3 . -Remove the- preser~a~ion and clean- the propeLler ( see

propeller MM, section 061.10.00).

8.4.2.4. Bleed the suction piping of the hydrulic system

according to the aircraft MM, section 029.00.00.

8.4.2.5. Refill nitrogen in the hydraulic accumulators (see I

aircraft MM, section 029.00.00). I

8.4.2.6. Check the cabin fire extinguisher. I

8.4.2.7, Carry o u t the engine t e s t lsee aircraft - - MM, - section - I - - - -

071.00.00). I

Jan 12/02 Page 8-7


EISLINTENANCE SCHEDULE

8.4.3. Work done after storinq the aircraft for a duration over 3

months

8.4.3.1. Carry out operations according to items 8.4.2.1. to

I 8.4.2.7.

8.4.3.2. Remove the preservation of enginesfrom outSide.While - - - - - - - - - - - - - - - - -

- - - - - -

- - - - - - -

doing so protect the electric installation and the

ignition system against the penetration of petrol.

8.4.3.3. Grease the mainwheel and nose wheel bearings.

8.4.3.4. Carry out the test flight. The, program of the

test flight is given in the separate document Check

Flight Methodics for the L 410 UVP-E20 aeroplane ' I .

Page 8-8 Jan 12/02

LET L 410 UVP-E20


Aug 31/95

S U P P L E M E N T S

Page 9-1

LET L 410 WP-E20



I Page 9-2

LET L 410 UVP-E2O

PJIAINTENANCE SCHEDULE

Lubrication plan

9.1.1. General

The lubrication plan consists of:

- survey of lubricated places, arranged according to the

type of joints

- lubrication tables, arranged according to types of - - - - - - - - -

inspection of the-periodic maintenance - - -

- - - - -

- tables of lubricated places, the lubrication of which is done in another interval than 300 hours.

9.1.2. Survey of lubricated places

The survey of lubricated places is arranged according to

the type of joints. The joint type is given by the first

figure of the triplace numerical marking of the joint:

lxx ..... hinged bearings 2xx ..... ball bearings 3xx ..... tapered roller bearings

- - - -4xx.; .; .grease nipples- - - - - - - - - - - - - - - - -

5xx ..... cables, bowden cable 6xx ..... hinges, bolts, sliding parts 7xx.....renewal of preservation of bolts and hinges

The illustration of lubricated places is in figures

9.1.-1 to 9.1.-10. To this survey belong the tables

9.1.3., 9.1.4. where the individual lubricated places

expressed by numbers,( corresponding to this survey) are

arranged into columns according to the periodicity

maintenance - inspection.

- Aug 31/95 Page 9.1-1

Number 3f lubrid. places.

Page 9.1-2

LET L 410 UVP-E20


Name

- - -

Hinsed bearinqs

on the pull rods of the control of rolling tab

on the cylinder of ground spoiler control

on the pull rods of closing of covers of the main landing gear

on the working cylinder of the main landing gear

suspensions of the covers of the nose landing gear

suspension of the countershaft for closing the covers of the nose landing gear

on the pull-rods of closing the nose landing gear covers on the pull-rod of the nose landing gear control

on the pull-rod of the cylinder of the nose landing gear servo-drive

on the pull-rods between the block of foot control and the column of the manual control (control system of the nose wheel from pedals)

on the pull-rods of the engine control

in the hinged joints of the fixing of teleflex of propeller control to the engine

control suspension of the rudder

Pcs gumber of figure

Aug 31/95

Number ~f lubrid . places.



Name

on the lever and on the pull-rod of controlling the trim tab of the aileron

suspensions of the aileron trim tab

on connecting pull-rods of the control of wing flaps

on the strut of the front baggage compartment door

suspension of the working cylinder of the nose landing gear

Ball bearinqs

- it is carried out during airplane inspection

elevator suspensions

rudder suspensions

on the pull-rod of the control of trim tabs of the rudder and inside of it

suspensions of ailerons

suspensions of wing flaps (except the suspensions at the frame No. 10)

on the pull-rod of the control of wing flaps


on the lever of the trim tab control (elevator)


Pcs !?umber of figure

Jan 12/02 Page 9.1-3

Number >f lubrid. places.

Page 9.1-4



Name

on the pulleys of the control system of the de-icing of engine air inlet

on the pull-rod of the elevator control

on the lever of the elevator control

on the pull-rod of aileron

on the pull-rod of the trim tab control of elevator

lower bearings of the rudder

on the pull-rod of the trim tab ' control of the rudder-at the trim tab

on the countershaft of the rudder trim tab control in rudder

on the pull-rod of ground spoiler control between the 14th and 15th rib

suspensions of wing flaps at the 10th rib


countershaft of the nose wheel control

Pcs Number of figure

Jan 12/02

Number >f lubrid. places.



Name

Tapered roller bearinqs

in the wheel of the main landing gear

in the wheel of the nose landing gear

Grease nipples

on the pull-rods of the heating control

on the brake pedals

on the drum of trim tab control (in the stabilizer)

on the pull-rods of engine air intake de-icing /ice separator vane/

on the leg of the main landing gear

on the leg of the nose landing gear and lock of the nose landing gear

on the leg of the nose landing gear


Cables, bowden cables

cables the aircraft control

cables of engine control

bowden cable of the mechanical indicator of the nose landing gear

Piano hinqes, bolts, slidins parts

spring stop in the control of the elevator (on the rear stop under the floor of the pilot's cockpit)

Pcs Jumber of figure

Jan 12/02 Page 9.1-5

Number of lubrid places.

Page 9.1-6

LET L 410 UVP-E20


- --

Name

lever pin of pulleys of the de-icing of the engine air intake

shaft of the GA-211A-00-4 mechanical windshield wiper

bearing of the rotating signal system of ice rotary- detector - - - ~ ~ ~ ~ ~ ~ ~

sliding parts of the wiper arms

suspension of the cover of main landing gear

lever pin of the cover of main landing gear

pin of the mechanical indicator of the main landing gear

sliding parts of the main landing gear lock

pins of the rear cover of the nose landing gear with the pull-rod

pins of the lever system of the servodrive of nose wheel

shaft in the box of the SKP 1 (8) limit switches and in the B 062 266 N braket

universal quick-release locks of covers on the fuselage (for the access to board batteries, radio equipment etc) piano hinges of the lower engine cowls and-theirvanes - - - - - - - ~ - ~ ~ ~ ~

piano hinges of suspensions of the olevator trim tab

piano hinge of the suspension of the rudder trim tab


Aug 31/95

Number ~f lubrid. places.


IXAINTENANCE S C H E D U L E

Name

?iano hinge of the ground spoiler

sliding parts of control levers in the ?ilotls cockpit. The friction lever nust not be greased.

sliding parts of the engine controls including the propeller reversing cam

suspensions of toilet door

suspensions of door in the partition ~etween the pilots and passengers

suspensions of the main entry and zmergency doors

fixing of the electro-mechanical strut in the rudder and left airleron

pivots locks engine cowls

tightening screws of fuel tanks and ~f water injection tank closures

lever of the drive of the trim tab position transmitter

zountershaft of the L 410.5350-01 nose wheel control


Pcs !?umber of figure

Jan 12/02 Page 9.1-7

Number 3f lubrid. places.



Name

levers the heating control

- it is carried out during airpla inspection

. ne

rear - - -

Renewal of bolt and hinqe preservation

horizontal stabilizer/fuselage attachment

vertical fin/fuselage attachment

pin of the rudder upper suspension (without removal)

engine mount /wing attachment

ABC tab attachment

main landing gear shock absorber lower attachment joint

connection of the front baggage compartment door with the fuselage

connection - of- the nose tilting cone with the fuselage


) Page 9.1-8 Jan 12/02



9.1.3. Lubrication tables arranqed accordinq to the types of

periodic maintenance (2, 3, 4)

Scheduled work

1. Wash with cleaning petrol and grease with the CIATIM 201 grease. The lubrication place 217 to be lubricated with type of maintenance 3 and 4 by means of a syringe - see MM aircraft subgroup 027.21.00 page 301 to 304.

Type of periodic maintenance

(lubrication place)

Jan 12/02 Page 9.1-9



Scheduled work


(lubrication place)

-

2. After dismantling the connecting parts wash with petrol and grease with the CIATIM 201 grease.

When cleaning and lubricating the extreme bearings of elevator (lubrication place 2 0 2 ) remove the duster (see detail B in fig. 9.1-1) and push it back into hole in the rib after lubrication.

3 . After dismantling the connecting parts wash with cleaning petrol and grease with MOLYKA (paste) or the VNIIP - 2 2 5 or the VNIIP - 2 3 2 .

) Page 9.1-10 Jan 12/02



Scheduled work

2. Wash with petrol and lubricate with the MK-8 oil. At lubrication places 606, 616, 617 rotate with the wire of the hinge. Lubricate the lubrication place 601 with a mixture of the CIATIM 201 grease and the KONKOR 101 preserving oil. Lubricate the lubrication place 626 with the AMG 10 hydraulic liquid. The lubrication place 637 to be lubricated the KONKOR 101 preserving oil by means of a syringe and blow away oil by air-pump.

5. Loosen the locks of the nose cover of the fuselage and turn the nose cover so that the sensor of the rotary ice detector aims askew upwards. Switch on the signal device of the LUN 1771.3-8 or the LUN 1771.4-8 rotary ice detector and put a few drops of the oil 132-8 on the outer accessible friction surface of the rotating sensor.

6. Remove the screw at the end of the GA-211A-00-4 windshield wiper shaft and press CIATIM 201 grease into the hole.

7. Wipe, using a clean cloth and lubricate, using the CIATIM 201 grease, the grease nipples with grease gun.


(lubrication place)

Jan 12/02 Page



Scheduled work

- - - - -

8. Clean with a clean cloth and grease with MLO-ELASTIK-R or CIATIM 201. At inaccessible places the MK-8 oil and a syringe with a piece of plastic tubing instead of the needle. The lubrication is important to be done mainly in places where cables pass over the rollers.

9. Clean with petrol and preserve with vaseline (e.g. L or KI 77 preservative vaseline). Lubricate the place 706 by by means of a syringe with KONKOR 101 preservative oil.

10.Wash the bearings with petrol and fill them up with the NH-2 grease all the year round. Note: As a substitute grease

one may use at temperature above -25O~ the NK-50 grease and at tem eratures below g -25 C a mixture of the NK-50 grease and 25% of the CIATIM 201 grease.

11.Wash with petrol and preserve with the KONKOR 101 or the MK-8 oil.


(lubrication place)

I Page 9.1-12 Jan 12/02

LET L 410 UVP-E20


9.1.4. Tables of lubrication points, the lubrication of which is

done in another interval than 300 hours

- lubrication done once a month ---- -

Scheduled work

Wipe with clean cloth and using the CIATIM 201 grease, lubricate the nipples with grease gun

Wash with cleaning petrol and grease with CIATIM 201

Wash with cleaning petrol and grease with the MOLYKA or the VNIINP-225 (232) compound

Wash with cleaning petrol and grease by means of a grease gun the nipples with 3cm3 of the CIATIM 201, the landing gear being set in the straight direction and both extreme positions.

Lubrication point

Note: */ If you are not sure that the joint is thoroughly lubricated, remove the lubricating nipple, clean the channel by means of a wire and repeat the lubrication. If the process was not successful, dismantle the critical joint, wash it with cleaning petrol throughly, assemble the joint and lubricate again. Carry out the lubrication once per two weeks in a sand environment.

lubrication done with any enqine replacement

I Scheduled work 1 Lubrication point I

9 . 1 . 5 . Lubrication dependinq on the season of the year

If the plane has not flown the number of flight hours in the bellow mentoned calendar period, it is neccesary to carry out lubrication which corresponds to these flight hours : 1 x in 6 months lubrication as per check 2 1 x in 2 years lubrication as per check 3 1 x in 4 years lubrication as per check 4

1. Clean with cleaning petrol and preserve with vaseline (e.g. the L or K-17 preservative vaseline)

- May 15/98

705

Page 9.1-13

LET L 410 UVP-E20


F i g . 9.1 - 1 TAIL UNIT A - detail of the rudder trim tab control assembly

B - detail of the elevator outer hinge bearing with the dust - cap

Page 9.1-14 Aug 31/95

LET L 410 UVP-E20


F i g . 9.1 - 4 NOSE WHEEL STEERING

- Aug 31/95 Page 9.1-17

LET L 410 W P - E 2 0


Fig. 9.1 - 5 MAIN LANDING GEAR

- Page 9.1-18 Aug 31/95



Fig. 9.1 - 2 AIRCRAFT CONTROLS A - Block of t h e hand and f o o t c o n t r o l

J a n 1 2 / 0 2 Page 9.1-15



Fig. 9.1 - 3 'WING

Page 9.1-16 Jan 12/02

LET L 410 UVP-E2O


9.1 - 6 NOSE LANDING GEAR

Page 9.1-19

LET L 410 UVP-E20


F I G . 9.1 - 7 ENGINE CONTROLS AND ENGINE COWLINGS

- Page 9.1-20 Aug 3 1 / 9 5

LET L 410 UVP-E2O

ISAINTENANCE SCHEDULE

Fig. 9.1 - 8 ENGINE NACELLE A - Detail of hinged joint of the teleflex mounting

- Aug 31/95 Page 9.1-21

LET L 410 UVP-E20


I 9 . 1 - 9 FUSELAGE FRONT SECTION

I A - detail of mechanical windshield wiper

- I I Page 9 .1 -22 Aug 3 1 / 9 5

LET L 410 UVP-E20


Fig. 9.1 - 10 DOOR AND FRONT AIRCRAFT TILTING CONE

Page 9 . 1 - 2 3

LET L 410 UVP-E20


- I

I Page 9.1-24


Aug 31/95


MSLINTENANCE S C H E D U L E

1 9.2. List of works after which it is necessary to carry out

weiqhinq of aircraft, levellins of aircraft and service

test fliqht

9.2.1. General

Carry out weighing of the aircraft in the following cases:

- after the adaption of the aircraft to another version or modification

- after the performed inspection of the aircraft - after replacing the wing

Carry out levelling of the aircraft in the following

cases:

- after the performed inspection of the aircraft - after emergency cases given in the para 7 of this

Maintenance Schedule

- after replacing the

Carry out the service

- after the performed - if the aircraft has - after the execution 9.2.4.1

- after the performed

wing, stabilizer, tail unit

test flight in the following cases:

periodic maintenance - checks 3, 4 been stored for more than 3 months

of works which are specified in item

inspection of the aircraft

9.2.2. Weiqhinq of aircraft

9.2.2.1. Check the state of the empty equipped aircraft.

Note : The weight of the empty equipped aircraft is

defined in the Flight Manual of

the L 410 UVP-E20 aircraft.

Jan 12/02 Page 9.2-1

LETECKE ZAVODY a.s. L 4 1 0 UVP-E20


9 .2 .2 .2 . Drain off all fuel.

9 . 2 . 2 . 3 . Fill up the undischargeable fuel amount

(left side - main fuel tanks 6 litres

wing tip tank 2,4 litre

right side - main fuel tanks 6 litres

wing tip tank - - - - - - - - - - - - - - - - - - - - - - - - - - 2,4 litre)

9 . 2 . 2 . 4 . Tare the balance.

9 .2 .2 .5 . Lift the aircraft on jacks.

9 .2 .2 .6 . Set the aircraft to cross plane by means of levelling

points No. 1 9 on the left and right wing with a maximum

difference of 1 mm.

9.2 .2 .7 . Set the aircraft to longitudinal plane by means of

levelling points on the fuselage No. 1 and No. 7 with a - - - ~ ~ ~

- - - - -

- maximum difference of 1 mm.

9 . 2 . 2 . 8 . Secure the jacks.

9 .2 .2 .9 . Check three times the found reactions. Record the result

into the Weight and Balance Record, carry out the

calculation of the weight of the empty aircraft and

determine the position of its centre of gravity in %

MAC.

9 . 2 . 2 . 1 0 . The results of weight and balance found by the

- - - - - - calculation record into the Flight Manual of tlik

L 4 1 0 WP-E20 aircraft, i.e. the weight and centre of

gravity in % MAC.

Page 9.2-2 Jan 1 2 / 0 2



9.2.3. Levellinq of aircraft

9.2.3.1. Check whether the aircraft is empty in the basic

configuration.

9.2.3.2. Discharge the fuel from the aircraft.

9.2.3.3. Lift the aircraft on jacks.

9.2.3.4. Set the aircraft to the crossplane by means of levelling

points No. 19 on the left and right wing with a maximum

difference of 1 mm.

9.2.3.5. Set the aircraft to the longitudinal plane of the

fuselage by means of levelling points No. 1 and 7 with a

maximum difference of 1 mm.

9.2.3.6. Secure the jacks.

9.2.3.7. Carry out levelling according to the Levelling and

Rigging Record of the aircraft and record the measured

values.

9.2.3.8. Compare the measured values with the values given in the

Record of the aircraft.

In case of exceeding the permissible tolerances it is

necessary to get the expert opinion of the manufacturer.

Jan 12/02 Page 9.2-3


I?/LAINTENANCE SCHEDULE

9 .2 .4 . O~eration check

9 . 2 . 4 . 1 . List of products after replacement of which carry out the service test flight.

I M 601 E or M-6llf E-21 Engine

No. of subgroup PTP

Replacement - - - - - - - - - - of one pr both -engines

Name of product and marking

Propeller

Works after the execution of which it is necessary to carry out the service test flight

Fuel regulator

Replacement of one or both propellers

Replacement of the regulator of one or both engines

1 Wing l~e~lacement of wing

Propeller Speed regulator

1 Stabilizer (Replacement of stabilizer

Replacement of one or both propeller regulators

I Replacement - - - - - - of the -fin

Replacement of elevator

l Rudder l~e~lacement of rudder

1 Ailerons Replacement of one or both ailerons

Operating test flight is performed as well as after exchange of every instrument whose setting or adjusting depends on the influence of aerodinamic forces in flight.

Wing flaps

Page 9.2 -4

Replacement of the inner or outer wing flap or slot

Jan 1 2 / 0 2 R



9.2.4.2. Proqram of operation check fliqhts

The program of the operation check flight (test flight) (see item 1.1.3.2.h) includes the recommended ways of the verification of the operation of individual aircraft systems, indicated values and aircraft characteristics during the flight. The aeroplane must be completed and equipped. The operator may according to his conditions adjust or supplement the operation check flight. All values found during the ground and flight tests should be recorded in the final internal certificate.

Jan 12/02 Page 9.2-5




1 Page 9.2-6 Jan 12/02

LET L 410 UVP-E20


The L 41 0 UVP-E20 Aeroplane

LEVELLING AND RIGGING RECORD

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aeroplane Serial No.:

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Registration Mark:

Page 9 . 2 - 7

LET L 410 UVP-E2O


Example of Levelling and Rigging Record (page 2)

1. Aeroplane l e v e l l i n q

1.1. L a t e r a l datum i s de termined by l e v e l l i n g p o i n t s go. 19 LX

and 1 9 RH / s e e F ig . 3 /

1 . 2 . L o g i t u d i n a l datum i s g iven by t h e f u s e l z g e datum I1

de te rmined by l e v e l l i n g p o i n t s L? No. 1 and 7 s e e F i q . !

whose p o s i t i o n s a r e s p e z i f i e d i n t h e tab12 on Page 8 .

I - L e v e l l i n g p l a n e / p a s s i n g through 1 .eve l l ing 2 o i n t s Xo . 3 , . 5 , 6 /

I1 - F u s e l q e datum / l i e s 10 mrn below t h e l e v e l l i n g p l ane /

I11 - Engine r i g g i n g f a c e t

Notes: - The v a l u e s i n t a b l e s f o r v e r t i c a l measurements r e f e r

t o t h e l e v e l l i n g p l a n e .

- The v a l n e s r e f e r r i n g t o l e v e l l i n g p o i n t s l y i n g below

t h e l e v e l l i n g p i a n e a r e ~ a r k e d x i t h , t h e s i g n "-". - The v a l u e s t o t h e l e f t 3.re marked w i t h t h e s i g n "-",

t o t h e r i g h t "+" / t h e LH and ?,H s i d e s a r e i d e n t i c a l

- s e e F i g . 2 .

Fig . 1

Page 9.2-8 Aug 31/95

LET L 410 UVP-E2O


Example of Levelling and ~igging Record (page 3)

2 . Check o f w i n q tip f u e l t a n k s p o s i t i o n r e l a t i v e t o l e v e l l i n q

p l a n e - see F i q . 1

CAUTION: FOLLOVTING TABLE LDPLIZS FOR Z R O P L X T S a3C.M. 16th S E R I Z S - - - - - - - - - - - - - - -

WITH WING T I ? FUEL TAX'XS FROM ~ ~ R I A L ~ 5 . - 8 b 1 6 0 1 , - - -

Nominal Yeasurenent ? ! e a s u z e ~ e n ~ i Xeasuremenc ~1 ignment I ! SO. 1 go. 2 No. 3

Check o f w inq t i p f u e l t a n k a x i s a l i g n m e n t r e l d t i v s t o t h e

l e v e l l i n q p l a n e - see F i g . L

CAPTION: FDLLOWIXG TABLE- A P P L I Z S ?OR- m-ROPLl2;ZS - - - - F2CX - - 1 6 - t h S E X I Z S - - - -

WITH W I N G T I P FUEL TAMS FROM SERIAL No. 8 6 1 6 0 1 .

Aug 31/95

F r o n t l e v e l l i n g po i n c

Rear Leve l l ing p o i n t

Page 9 . 2 - 9

Diffe- rence

64 .78

64.78

Tole- r a n c e

210

210

Xeasurernent Yo. 1

LH!

Uezsurement So. 2

1

Xeasurement No. ?

Xd I

LET L 410 UVP-E20

M2lINTENANCE SCHEDULE

Example of ~evelling and ~igging Record (page 4)

4 . Check of wing t i p f u e l t anks p o s i t i o n r e l a t i v e t o t h e

a e r o p l a n e a x i s - s e e F i g . 2

CAUTION: FOLLOWING TABLE APPLIES FOR AEROPLANES FROM 1 6 t h SZRIZS

W I T H W I N G TIP FUEL TANKS FSOM SZZIXL No. 851601.

5. Check o f Aliqnment D /measured i n t h e ~ r o u e l l e r s h a f t a x i s /

Check of Alignment E /measured from p lane I1 t o III/ - - s e e F i g . 1

Nominal Xeasurement Yeasurement .Neasurement NO. 2 I N o . 3

r A 1 ignment

The d i f f e r e n c e between D and E must n o t exceed 3 nun.

The. a l i gnmen t t o be checked p r i o r t h e 3 r a n e l l e r i n s t a l l a t i o n .

Page 9.2-10

Yeasurement Xo. 3

Nominal value

Yeasurement !'a. 1

Tolerance Yeasurenent

Yo. 2

LET L 410 UVP-E20

-1NTENANCE SCHEDULE - -

Example of ~evelling and Rigging Record (page 5)

6. Check of fuse lage sag and ~ w i s t - see F i q . 1

7. Check of s t a t i c p r e s s u r s head ? o s i t i o n - see ?ig. 1

Nominal Ileasur-.=enc >!easur+3enc !-!easurenec h l ignmen t !lo. 2 90. 3

A u g 31/95 Page 9.2-11

LET L 410 UVP-E20



0 - 1 9 9 7 9 . 5 / t h e o r e t i c d imens ion/ - f o r a e r o p l a n e s w i t h

wing t i p f u e l t a n k s

I! - 1 9 4 7 8 . 9 / t h e o r e t i c d imens ion/ - for a e r o p l a n e s with

wing t i p s

Page 9.2-12 A u g 31/95

LET L 410 UVP-E20



8. Check of alignments F, G /measured in the propeller shaf' axis

- see F'icl. 2

L T L e r a n c e I :4e.asurcment / ueasurenent I ~easurezent / Yo. 1 Yo. 2 !lo. 3

The check of engine alignment to be carried out prior the propeller installation.

9 . Check of alignments A, B - see 'ig. 2

Subcript L = left hand, ? = right hand side.

r

Alignment

A

.\ - .$

B

BL - Bp

Page 9 . 2 - 1 3

Tolerance

Xax.difference 15

Xax.difference 15

7

. Yeasurement Yo. 3

- xi

ItY

LX

w

Xeasurement Y o , I

I

Measure3enc No. 2

LET L 410 W P - E 2 0

M.AINTENANCE SCHEDULE -


10. C h e c k of fuselage curvature - s e e F i c . 2

11. C h e c k of w i n g twist - see Fig. 3

,eve11 ing p o i n t s

ioninal !!easuremsnc Lfeasurernent Xeasurement Tolerance value Yo. 1 Yo. 2 ?To. 3

I mi + 4 . 20.25 -

I 5 3

ii 1 + 4 1 3 . 9 8 -

824 1 LII

+ 4 - 1 .oo -

Page 9.2-14 Aug 3 1 / 9 5

LET L 410 UVP-E20

I??LAINTENANCE SCHEDULE


12. Check of s t a b i l i z e r t v i s z I?.< 2 i h e d r a l t o s e c g r s a 2.j a n g l e

o f i nc idence - s e e Pic. 3

Level 1 in: A 1 ignmen t po i n t s

23-24 lower

13. Check of s t a b i l i z e r ?oslz.:c?. z s l z t i v e ?o I ? v e l l i n g e l x e

Yominal Xeasurezent / :g cranc va lue

I I 2i 4 2 . 3 7 ' - 3

t o s e c u r e a 2" a n g l e oE inc l j ,ance - s e e ? i ~ . 2

>!easnrernent 3easurenent So. 2

1 1 !TO. 3

I

I

I Level1 ing A 1 ignnen t

p o i n t s

lower I 23

Yoninz, , ' / Xeasurezecx tl U e a s u r e ~ ~ ~ t !-feasurernenc

- a ; s i m c e i i ,- val ~e .do. i I Y O . 2 YO. 3

i

L . 1 i

. 2 8 . 7

A u g 31/95 Page 9.2-15

iH

I i

LET L 410 UVP-E20



F i g . 3

14. Check of aliqnment C - see Pig. 3

A 1 ignmen t

Page 9.2-16

Tolerance 0 1 i

VC?

Aug 31/95

I I

%..lax. difference 15 .,

LET L 410 UVP-E20



1 5 . Check o f winq p o s i t i o n r e l a t i v e t o t h e l e v e l l i n c p l a n e ,

a n g l e of d i h e d r a l - s e e T i c . 3

CAUTION: FOLLOWING TABLE A P P L I E S FOR AEROPLXUES FRCX 1 6 ~ 5 SZ?.IXS WITH WING T I P F C E L T.AN:<S ??.OM S E X I X L N O . 3 6 1 6 0 1 .

Xorninal To lz rance .easurement Ueasurmenc v a l u e ? r ~ a . } Oper. - - - - Yo. I Yo. 2 Yo. 3

Page 9.2-17 Aug 31 /95

LET L 410 UVP-E2O



Values w i t h o u t i d e n t i f i c a t i o n a p p l y for l e v e l l i n g p o i n t s

11- - 2 0 o n a e r o p l a n e s w i t h o u t Wing tip f u e l t a n k s .

Va lues i d e n t i f i e d w i t h * a p p l y f o r l e v e l l i n g p o i n t s

11 - 2 0 on a e r o p l a n e s w i t h wing t i p f u e l t a n k s .

I d e n t i f y v a l u e s i n t h e t a b l e , measured on a e r o p l a n e w i t h

wing t i p f u e l t a n k s with * .

1 6 . Check of wing p o s i t i o n - see F i g . 3

1 7 . Check of l a n d i n g gear fmss su red i n &loaded c o n d i t i o n / - - -

- s e e F i g . 3

I

A1 i gnmen t

3

Page 9.2-18

Prod. = P r o d u c t i o n ; Oper. = Opera t i on

L e v e l l i n g p o i n t s

19-1 1

A1 ignment

Aug 3 1 / 9 5

Xorninal v a l u e

293'55 287.55*

9

YOminal v a l u e

T o l e r a . ~ c e

Tolerance 1 Xeasureaent Yo. 1

Yeasurenent No. 1

LX . xi

Prod.

+ 10 -

Xeasurement ?lo. 2 Oper.

2 28

Xeasurement Yo. 2

Xeasurement YO. 3

Yeasurement Xo. 3

U J i i

L 410 UVP-E20 m I N T E N A N C E SCHEDULE


l a . Check of r u d d e r a n d r u d d e r t r i m tab def1ec:icns - s e e F i g . 4

XorninaL Tol_era_nce_

Xeasurezent !!easare~ent . X e a s u r e ~ e n c 11 ignmen t Angle v a l u e -

o 1 - - -YO? 7 - - - X O - 3 -

The v a l u e s of a n g l e s a r e s 3 e c i f i e d i n h c r l z c n t a l ?La?-=.

The v a l u e X = 2 5 - 2 . 5 mi 2 e a s u r s d on t he u g p e r Itf = end

of che ~ r L 3 tab. . . X = 25 - 3 . 9 m a 2 a s u r e d on =he - ? p e r r:q-r 2nd

of ~ 3 - e t r i n t 2b .

A u g 31/95 Page 9.2-19

LET L 410 UVP-E20

1 9 . Check of a i l e r o n and a i l e r o n t z i x t a b d e f l e c t i o n s

- s e e Fiq. 5

F i g . 5



d

I V - Wing datum

-

1 / omi in all Toierance/ / ~ e r s u r e r ; e n t Yersurernent Yeasurcreo t A 1 ignment Angle value

0 . 1 No. 2 Xo. 3

S u b s c r i p t H = up, D = down.

Page 9.2-20 Aug 31/95

LET L 410 UVP-E2O



2 0 . Chec!< of e l e v a t o r and e l e v a t o r t r i m t a b d e f l e c t i o n s - - see Fiq. 6

Fiq. 6

I1 = Fuselage datum

VI = Horizonta l s c a b i l i z e z datum

Xeasur+nent Xeasurement Xeasurernen ~ o l 2 r m c . j I No. I / 0 . 2 / Yo. 3 j

Subscript H = u p , D = EO:VT.

Page 9 . 2 - 2 1

2 1 . Nosewheel s t e e r i n g a n g l e - s e e f i g . 7

Y = manual mode

w = p e d a l mode

LET L 410 UVP-E20



F i g . 7

S u b s c r i p t L = l e f t h a n d , P = r i g h t hand s ide .

Page 9.2-22 Aug 31/95

LET L 410 UVP-E2O



2 2 . Check o f o u t e r and i n n e r x i n g f l a p d e f l e c t i o n s

2 2 . 1 . F l a p s i n t a k e - o f f p o s i t i o n - s e e Pig. 8

- Angle 6 1 l s p e c i f i e s t n e t a k e - o f f p o s i t i o n o f o u t e r f l a p s

- Angle 6 s p e c i f i e s the t + k e - o f f ? o s i t i o r , o f i n n e r f k 3 s

Page 9 . 2 - 2 3

+ ,

Alignment

2 0 u4.d !4 c o u w o

U rV .I w w u - 4 Mu + 8 . - C a J I I O .2J* =.

F l a p p o s i - t i o n

6 1 1

12

Yominal v a l u e o f t h e a n g l e

18' 1 - - l o w-

- measured I .iEi

- 1 - 1 - - 1 - 1 -

LET L 410 UVP-E2O



22.2. F l a p s i n l a n d i n g p o s i t i o n - s e e F ig . 9

- Angle 6 s p e c i f i e s t h e l a n d i n g p o s i t i o n of o u t e r f l a p s 2 1

- Angle 6 2 2 s p e c i f i e s t h e l a n d i n g p o s i t i o n of i n - e r f l a p s

- x/ Nominal v a l u e of a n g l e 6 2 2 e q u a l s v a l u e of r n g l e 6 2 1

obta,$ned d u r i n g measurements 30. ! / 2 , 3 / - lo0.

F i g . 9

Page 9 . 2 - 2 4 A u g 31/95

Alignment Tolerance Flap position

Xeasurement Zeasurenent No. 1 1 x 0 . 2

I

Nominal value o f angle

7

Xeasureaent No. 3

LET L 410 UVP-E20

MZkINTENANCE S C H E D U L E


Ueasurement Sfeasurement Ueasurement Xl i gnmen t NO. 1 No. 7 Yo. 3 I

Subscript L = left hand , 2 = - - --?:A- - - - s i d e .

Page 9 . 2 - 2 5

LET L 410 UVP-E20


Example of Levelling and ~igging Record (page 20)

2 4 . Check o f a u t o m a t i c bank c o n t r o l t a b d e f l e c t i o n - see P i g . 1 1

F i g . 11

S u b s c r i p t L = l e f t hand , P = r i g h t hand s i d e

C e r t i f i c a t e o f measurement c o r r e c t u e s s

Measurement Measurement I N 0 . i 1 N o . 2 N o . 3

Date

O r g a n i z a t i o n :

S i q n a t u r e o f t h e r e s p o n - s i b l e p e r s o n

Page 9.2-26 A u g 31/95

LET L 410 UVP-E2O


9.2.4. Operation check

9.2.4.1. List of products after replacement of which carry out the service test flight.

No. of subgroup PTP

Name of product and marking

M 601 E or M 601 E-21 Engine

Fuel regulator

Propeller

Propeller Speed regulator

Wing

Stabilizer

Fin

Elevator

Rudder

Ailerons

Wing flaps

Works after the execution of which it is necessary to carry out the service test flight

Replacement of one or both engines

Replacement of the regulator of one or both engines

Replacement of one or both propellers

Replacement of one or both propeller regulators

Replacement of wing

Replacement of stabilizer

Replacement of the fin

Replacement of elevator

Replacement of rudder

Replacement of one or both ailerons

Replacement of the inner or outer wing flap or slot

Operating test flight is performed as well as after exchange of every instrument whose setting or adjusting depends on the influence of aerodinamic forces in flight.

- Jul 15/99 Page 9.2-27

LET L 410 UVP-E20


9.2.4.2. Proqram of operation check fliqhts

The program of the operation check flight includes the

recommended ways of the verification of the operation of

individual aircraft systems, indicated values and

properties during the flight. - - - - - - - - - - - -

The results o f - the check and their e~~luations should be

done in accordance with the Flight Manual of the

L 410 WP-E20 aeroplane.

CAUTION: ALL LIMITATIONS GIVEN IN THE FLIGHT MANUAL OF

THE L 410 WP-E20 AEROPLANE MUST BE KEPT DURING

THE CHECK FLIGHT.

I - I I P a g e 9 . 2 - 2 8 Aug 31/95

LET L 410 WP-E20


Name of work (check)

WORK SET-UP Routine maintenance A,C

Engine test - - - - - - - - - - - -

Check of the automatic feathering and automatic bank control.

Test of the IELU

Filling-up with fuel for the check of fuel transfer from wing tip tanks

CHECK FLIGHT

Starting

Check of engine starting

Zheck of the IELU

Taxiing

Reason of check flight

Page 9 . 2 - 2 9

LET L 410 UVP-E20



t

13 Check of brake operation

14 Nose wheel manual steering check

15 "BETA RANGE" signalling check

16 Nose wheel pedal steering check during take-off

17 Check of engine and propeller performance during take-of f power setting

Landing gear and wing flaps retraction check

- Page 9.2-30

Reason of the check flight

Aug 31/95

LET L 410 UVP-E20



Check of pedal steering control force during take-off

Altitude 2000 m ISA

Altitude 3000 m ISA

Altitude 3000 m ISA

Check of engine and propeller performance at Maximum Continuous power

Check of windscreen heating

Check of propeller deicing

Check of the airframe and engine deicing


Page 9 . 2 - 3 1

LET L 410 WP-E20



Check of operation and efficiency of heating in the cockpit and pasenger compartment

- - -

Check of oil- temperature increase with ice separator vanes in open position

Check of fuel crossfeed and fuel pumps switching-off

Check of engine operation at Maximum Continuous power and idle at v=200 km/h IAS

- - - - -

Check-of acceleration- -transfer of POWER control lever within 3 s

Page 9.2-32


Aug 31/95

Lllr'L

L 410 UVP-E20 MAINTENANCE SCHEDULE


Descent

Check of the aeroplane ability to trim at idle -

- - - - -

Horizontal take-off

Verification of acceleration

In-flight engine starting check

Descent

Acceleration of the flight to V ,,=370 km/hr IAS. ~ g e c k of the response of the aeroplane in dependence on elevator control force


Aug 31/95 Page 9 . 2 - 3 3 I

LET L 410 UVP-E20



Acceleration of the flight to ax =350 km/hr I A S

deck of the response of the aeroplane in dependence on elevator control force

Cruise

Check of ability to trim and control of the aircraft

3 4 Check of engine and propeller performance at Maximum Continuous power

-

Page 9.2-34

3 6

37


POWER control lever and PROP control lever setting check

Flight check

A u g 31/95

LET L 410 WP-E2O

PJILAINTENANCE SCHEDULE


Emergency fuel control circuit check-engine control

Radio navigation and communication equipment check

Check of stall characteristics in ind. flight configurations. Check of stall speed warning adjustment

Automatic feathering check, automatic bank control operation check. Adjustment of automatic feathering switches

Landing gear extension/retraction check at flight with one engine inoperative


Page 9 . 2 - 3 5

LET L 410 WP-E20



Check of operation of ILS, radio altimeter, audio switch box, special equipment

Check of - fuel transfer from wing tip tanks during the flight

Descent

Check of propeller minimum flight angle stop adjustment

Check of propeller operation at go/around

Check of emergency landing gear and

- - -

wing flaps- extension

Page 9.2-36


Aug 31/95

LET L 410 WP-E20




Check of operation of automatic blocking of the win2 flaps extension and of the securing of landing gear

Landing

Ground spoiler operation check

BETA signalling and reverse range check

The brake antiskid operation check

Check of propeller unit operation during aborted take-of f

Work close-up

Routine maintenance B

Page 9 . 2 - 3 7

LET L 410 WP-E2O



Evaluation of the correct pera at ion of the BUR-1-2G flight recorder


Page 9.2-38 A u g 31/95

LET L 410 UVP-E20


9.2.4.3. Operation check fliqht methodics

The methodics of operation check flights must correspond

to the procesures and limitations given in the Flight

Manual of the L 410 UVP-E20 aeroplane. The metodic

instructions include only detailing and supplementing

regulations. The aeroplane must be completed and

equipped. The operator may according to his conditions

adjust or supplement the operation check flight. All

values found during the ground and flight tests should

be recorded in the final internal certificate.

WORK SET-UP

04. Filling-up with fuel for the fuel transfer check from the

wing tip tanks.

Fill-up the fuel in following amounts:

- main fuel tanks 400 kg left side

400 kg right side

- wing tip tanks 50 kg left side

50 kg right side

CHECK FLIGHTS

Carry out the check flights with the mass and centre of gravity

XT= 26% MAC

Page 9.2-39

LET L 410 UVP-E20


The crew of the operation check flight is formed by 2 pilots and

expert workers securing the tasks given by the flight check. The

crew of the aircraft must have parachutes on board. With flights

above 3050 + - MSA the crew must use oxygen masks. The main technical data of M 601 E engines are speed nG%.

12. Check of the IELU (Integrated Electronic Limiter Unit)

12.1. In the course of starting the IELU must secure the

inter-turbine temperature gradient ITT in order not to

exceed the temperature values for starting. Follow the

increase of ITT.

12.2. Check of switching-on I level of limitation

- increase the speed of the gas generator by a slow

shifting of POWER control lever

- read the torque at which the signalling of the green

signal lamp goes on

- the value must be within limits 65 to 75% torque

17. Check of engine and propeller performance during take-off

power setting.

17.1. At the altitude of 500 m QFE record the value of the

maximum take-off power.

1 Page 9.2-40 Aug 31/95

LET L 410 UVP-E20


20. Check of engine and propeller performance at Maximum

Continuous power.

20.1. Record the values at the altitude of 2000 m.

I

25. Check of oil temperature increase with ice separator vanes in I - - - - - - - - - - - - - - - - - - -

- - - - -

I open position. - - - - - - - - -

25.1. When reaching the altitude of 2000 m open the ice separator

vanes and close then at 4000 m. Check the temperature

increase of oil which must not exceed the max. operational

value.

I 26. Check of fuel crossfeed and fuel pumps switching-off

26.1. Carry out at the altitude of 4000-5000 m. ~uring this check - - - - the - signaf FUEL - PRESSURE- en the - central warning display

must not light.

27. Check of engine operation at Maximum Continuous power and

idle at V = 200 km/hr I A S

27.1. Record the values shown at the Maximum Continuous power at

the altitude of 5000 m and at idle at V = 200 km/IAS.

28. Check of acceleration - transfer of POWER control lever - - - - - - - - - - - - - - - - - - - -

- - - - - - - - - -

within 3 sec

28.1. Check the acceleration at a slow - at least 3 sec- transfer of POWER control lever at the altitude of 5000 m and

V = 200 km/hhr IAS. - Aug 31/95 Page 9.2-41

LET L 410 UVP-E20


29. Check of the aeroplane ability to trim at idle

29.1. When descending from the altitude of 5000 m down to 4000 m

at idle engine power setting trim the aircraft to the max.

value TAIL-HEAVY.

The cruising speed must be 190 km/hr to 165 km/hr.

30. Verification of acceleration

30.1. Check the acceleration in the altitude of 4000 m

- verification of acceleration from idle, continuation of

run

- verification with switched-off fuel pumps; shifting of

POWER control levers in min. 3 sec

- verification of acceleration and time check max. 5 sec

from the initial rating for acceleration, i.e. 75% nG to

95% of max. take-off power at V = 200 km/hr. Shifting of

POWER control levers in 1 second.

31. In-flight engine starting check

31.1. Carry out at the altitude of 4000 m the following:

- carry out the procedure for manual feathering of

propeller

- engine shut-down

- starting the engine

-

Page 9.2-42 Aug 31/95

LET L 410 UVP-E20


Evaluate :

- starting time of ignition up to max. 12 sec. - course of starting - reached max. ITT temperature - time necessary for setting the propeller out of feathered position

32. Acceleration of aircraft to Vma,=370 km/hr IAS

Check of the response of the aeroplane in dependence on

elevator control force.

32.1. Verify:

The evaluation of the elevator control force in dependence

on cruising speed and the evaluation of the total aeroplane

and engine response.

- height balancing (trim) - neutral - engine power torque 80%, n -1800 RPM

prop- - permissible force max 10-20 N (1-2 kp)

33. Flight acceleration to Vmax=350 km/hr IAS. Check of the

response of the aeroplane in dependence on elevator control

force

33.1. The evalution of the dependence of the elevator control

force on the speed. The process is the same as item 32,

however, with reaching the speed Vma,=350 km/hr IAS.

Allowable force max. 10 N to 20 N (1 kp to 2 kp).

Page 9.2-43

LET L 410 UVP-E20


36. POWER control lever and PROP control lever setting check

36.1. Adjust the control levers in such a way that the difference

between them at the lever ends is max. 4 nun.

37. Flight check of propellers - - - - - - - - - - - - - - - - - - -

37.1. Carry out the check of the propeller operation and data in

accordance with the program of acceptation flight test of

the V 510 propeller given in the item 9.2.4.4.

39. Radio navigation and communication equipment check

39.1. Carry out in accordance with the regulations for the

built-in devices in the aircraft and with the Flight Manual

of the L 410 UVP-E20 aeroplane following the programm: - - - - - - - - - -

- - - - - - - - ~ ~

- - - - - - -

VHF Transceiver:

- check of the 2-way communication in a distance min 120 km at the altitude min. of 1000 m above the level of the

ground station at direct radio visibility

- check of interference during flight

Radiocompass:

- check of operation and bearing accuracy to ground NDB

beacon in a distanceof180 km atthe altitude of 1000 m - - - - - - - - - - -

above the ground NDB beacon (f -400 kHz)

- check of instability zone when flying over NDB

- Page 9.2-44 Aug 31/95

LET L 410 UVP-E20


Course system:

- liquid compass. When checking the deviation switch off

the wiper and fan

Navigation instruments:

- check of gyro horizon operation in all flight power

settings

- check and record of signalling values of limit banks.

Wing flaps o0 and 18O - check of the operation of turn-and-bank indicators in

all flights power settings

- check of operation and comparison of barometric

instruments in all flight power settings.

40. Check of stall characteristics in individual flight

configurations. Check of stall speed warning adjustment.

40.1. Flight configurations:

- engine idle power, landing gear retracted, wing flaps o0 - engine idle power, landing gear retracted, wing flaps

18O

- engine idle power, landing gear extended, wing flaps 42'

- nv=1800 RPM, torque = 41%, landing gear retracted, wing

flaps o0

Switch on signallization and carry out stall in the above

mentioned configurations. The signal of the stalling speed must

be adjusted so that it starts signalling at least at 15 km/hr

before the stalling speed.

Page 9.2-45

LET L 410 WP-E20


Stalling speeds - engine idle power

o0 - cruising 18O - take-off 42O - landing

Position of wing flaps:

41. Automatic feathering and automatic bank control operation

check

Stalling speed IAS (km/hr)

Adjustment of automatic feathering switches.

41.1. Imitate the failure with the PROP. FEATHERING-AUTO

push-button on the LH control panel and move the POWER

control lever to the idle-power position.

Set the POWER control lever so that the signalling of

automatic bank control and automatic feathering starts to

function. Revolutions nG at least 88 + - 1% or 92 + - 1% (difference between switching-on and off max. 4% nG). Set

the flight speed close below 200 km/hr. Imitate the

failure.

Check:

Check of the rudder trim tab efficiency (check of bank for

the straight forward flight with the max. trim tab

deflection with the max. take-off engine power and

V=200 km/hr IAS with a balanced flight).

Increase the flight speed and check the retraction of the

ABC tab at 205 + - 5 km/hr IAS.

I - I I Page 9.2-46 Aug 31/95

LET L 410 UVP-E20


43. Check of operation of ILS, radio altimeter audio switch box

and special equipment

43.1. ILS

- check of range. At least 48 km with the course receiver

in the balancing field of the ground beacon, at least

18,5 km with the descending receiver in the balancing

field of the ground beacon.

- check of accuracy of the guiding along the course and

slip. Visually or with PAR till the operation minima.

- check of the light and acoustic signalling of light

markers 75 MHz Marker. At an altitude of 600 m above the

approach marker. Signalling time 4 s at least.

43.2. Radio altimeter

- check and record of data in the working band of

altitudes 500 m, 300 m, 100 m, QFE (under VMC

conditions) above the airfield. Compare with the

electromechanical altimeter or barometric altimeter set

to QFE of the airfield

- check of the acoustic and light signalling at the

altitude of 60 m QFE above the airfield runway under VMC

conditions.

43.3. Special equipment

Check the operation of the BUR-1-2G flight recorder.

Page 9 .2 -47

LET L 410 UVP-E20


44. Check of fuel transfer from wing tip fuel tanks during the

flight

44.1 . Carry out at horizontal flight at about 300 km/hr IAS,

altitude 1500 to 2000 m. Switching-on green signal window

of fuel pumping must occur in the range of 4 0 0 to 2 7 0 kg

indicated on the indicators. The data on the scales must be

simultaneous. After completing the fuel transfer the signal

windows go off (not necessarily at the same time).

-

Page 9 .2 -48 Aug 31/95

LET L 410 WP-E20


9.2.4.4. Program of acceptance flight test of V 5 1 0 propeller

Power setting

Engine test

a/ Check of the propeller speed limiter without the closing nut of the limiter and front part of the propeller cock. -propeller control lever in position nvmax. -increase the generator speed by means of POWER control lever till the intervention of the limiter,further on increase nG still more by 2 % and then back to idle power -repeat five times on both units

b/ Check of deicing of propeller blades

To be checked

-in the 3rd to 5th transition n = 2 0 0 0 RPM

P

- Aug 3 1 / 9 5 Page 9 . 2 - 4 9

LET L 410 WP-E20


Power setting

I -propeller control lever in

I position n -enqine congrof lever at take- / -off power setting.

-altitude 1000 m QFE/FL 2000 m 3000 m

-v = 230 km/h -P@L in position nv = 1900 l/min -set the ELC to n = 97 % , lock both the levers.

ICruise and speed chanqe

(by pushing and pulling control column). -altitude 3000 to 2500 m -v = 300 + 40 km/hr - P ~ L in position n = 1800 l/min -set engine controy lever n = 94 % to 97 % g

Chanqe of speed of propeller control lever (PCL)

-altitude 3000 to 2500 m -v = 300 + 40 km/h -sRift PCL fluently from max. speed nv = 2080 to 1700 l/min and back -set ELC to n = 94 %

g

Page 9.2-50

To be checked

After reaching the speed of 150 km/h IAS the permissible values are as follows: -nV = 2080+20 l/min -difference of RPM left right hand side max. 20 RPM. -rotation overspeed is max. 2120+20 RPM

-speed shall be in tolerance range of + 15 RPM.

-in steady cruise speed n, = 1800 2 10 l/min -at change of speed n, = + 30 l/min.

-propeller speed in course of loading and unloading shall be in compliance witk movement of PCL -rea

Aug 31/95

LET L 410 WP-E20


Power setting

Power chanqe

-altitude 3000 to 2500 m -v = 300 km/h - P ~ L in position n, = 1800 l/min -shift ECL from n = 97 % to idle power and back wythin 10 s.

I Propeller f eatherinq a/ Automatic feathering

-altitude 3000 to 1500 m -v = 190 km/h - P ~ L in position nv max.

Preparation of feathering -perform in accordance with the Flight Manual L410 UVP-E20 aircraft

After propeller has been feathered (L.H.)-(R.H.) -v = 300 to 200 km/h iR horizontal, straight flight without slips.

Propeller setting out of feathered position and setting of flight mode -perform in accordance with the Flight Manunal L 410 UVP-E20 aircraft .

b/ Manual feathering: -altitude 4000 to 1500 m -v = 250 km/h - P ~ L in position np max.

Preparation for feathering -perform in compliance with the Flight Manual L410 UVP-E2C

To be checked

-till steady state (n = 1800 l/min) max. 3 ovgrshoots from the nominal value with tolerance + 30 l/min are permissible. -

-feathering time 5 s -signal cells on CWD are on

- np = max. 20 l/min in clockwise direction

- setting propeller out of feathered position

- time necessary for settins to the feather within 5 s

- cells on the CWD will be on.

Aug 31/95 Page 9.2-51

LET L 410 UVP-E20

M2iINTENANCE S C H E D U L E

Power setting

After propeller feathering (L.H.)-(R.H.) -v = 300 to 200 km/h hgrizontal ,straight flight without slips

Setting the propeller out of feathered position and setting

- - - - - - -

t h e flight mode -perform according to the Flight Manual for L410 UVP-E20 aircraft.

c / Emergency feathering -altitude 4000 to 1500 m -v = 300 km/h - P ~ L in position nv max.

Feathering -perform according to the Flight Manual for L410 UVP-E20 aircraft.

After propeller feathering (L.H.)-(R.H.) -v = 3-00 t o 2-00 km/h i-n hBrizantal, straight flight without any slips.

Propeller setting out of feathered position and flight mode setting -perform according to the Flight Manual for L410 WP-E20 aircraft.

Check of deicinq

-altitude 100 m QFE to FL 5000m -v = 190 to 350 km/h - P ~ L in position nv = 2080 to 1700 l/min - -

'switch -gradually the switch PROP DEICING STBY MAIN into positions I and I1 (interval I is 40 sfinterval I1 is 80 s) for the main and standby timer circuit, -perform check on each timer for 2 minutes.

Page 9 .2 -52

To be checked

- - --

- ny = 20 l/min in clockwise direction

- setting propeller out - - of feathered position

- time for setting to feathered position max. 20 s

- = max. 50 l/min in c " Y ockwlse . - direction

- setting the propeller out of feathered position.

- after firts cycle the cell PROPELLER DEICING on CWD goes off.

- - - - - - - - - ~ ~ ~ ~ ~

Aug 31/95

LET L 410 UVP-E20


Power setting

Check of fine pitch stop

Initial condition for both engines -altitude 1500 to 1200 m -PCL in position corresponding

= 2080 + 20 l/min -set CL to n = 95 % , then decrease sli3htly generator speed of appropriate unit.

Aborted Landinq

-altitude 500 m QFE -v = 180 km/h -&t PCL to position n max. -set ECL from flight i h e power rating to max. take off power within 1 to 2 s.

Reverse

-v = max. 140 km/h -mgve PCL to position nv max. -ECL in position idle power, after touching set the lever to max. reversion, after stopping set it back.

To be checked

- propeller operates as fixed-pitch propeller. The moment propeller speed dree will drop below the controllable speed,read

and indicated airspeed.

- max. 3 overshoots (nv = max.2200 l/min) from nominal value with tolerance + 10 l/min are permissible till reaching the steady condition. Total time to stabiliza- tion is max. 6 s.

- signal cell "BETA RANGEN wiil be on after the first transition phase of ECL (with increase in generator speed the propeller speed will rise on n max. = 1900 l/min.

- pgrmissible difference between propeller speeds is max. 10 l/min. at maximum reverse mode,

- idle speed after reverse Compare the idle speed with speed before take off.

Page 9.2-53

LET L 410 W P - E 2 O


Power setting

lborted take-of f

-take off run on a speed of v = 140 km/h at a height of oPm QFE -set PCL to position n max. -set ECL to take off pBwer position -then shift ECL smoothly with a max. rate to the stop of the conpled linhage and further on into the position max. reverse (within 2 s)

-after stopping shift ECL in front of idle power stop.

Jheck of propeller unit tiqhtness

-after acceptance flight

To be checked

- propellers speed shall not exceed value ny = 2080 l/min

- signal cell "BETA RANGE" will be on

- at v = 0 km/h(standstill) n, =Pmax. 1900 l/min.

- slgnal cell "BETA RANGEw will be of

- compare idle speed n with the speed before takg off.

- in according to VJ8.510

The given technical data must be maintained when testing the 9ropeller unit in flight. At service follow the Flight Manual L 410 UVP-E20 aircraft.

Page 9.2-54 Aug 31/95

LET L 410 UVP-E20

MJ i INTENANCE S C H E D U L E

May 15/98 Page 9.3-1

-

No.

-

3.

4.

5.

-

Name

Engine oil

Oil

Oil

Specification

(CR)

MK- 8

GOST 6457-66

Specification

(CIS)

Specification

(western)

b) Aeroshell

Turbine OIL 500

(555,560)

MIL-L 23699 D

(USA

DERD. 2499

(GB)

c) Mobile

JET Oil I1

MIL-L 23699 D

(USA

Exxon Turbo oil

2380,

Castrol 599.

Aeroshell

Turboil 3

DERD 2490,

Shell Oil

Ensis L,

Shell Storage

Oil 3.

Aeroshell

Compoud

MIL-G-16173A

Note

Mutual mixing

of oils groups

(a,b,c) is not

permitted

Application-

-stated in

Supplement 9.1

Application-

-stated in

Supplement 9.1

No.

-

6.

7.

Name

Oil

Zrease

Specification

(CR

CIATIM 201

ZOST 6267-74

Specification

(CIS)

CIATIM 201

GOST 2267-74

Specification

(western)

Aeroshell

Fluid 12

MIL-L6085A

ESSO Univis P12

MIL-L-6085 A

Aeroshell

Grease 6

MIL-G-7711 A

Aeroshell

Grease 22 or

22 c,

Mobil Grease 28

Braycote 622,

Nycogrease 22

MIL-G-81322.

Isoflex LD 318

special A.

Equivalent

specification:

DEF.STAN 91-51

(GB)

AIR 4222

( France )

NT-10006

(USA)

G-382

(NATO)

Note

Application-

-stated in

Supplement 9.1

Application-

-stated in

Supplement 9.1


Page 9.3-4 Jan 12/02

L 410 UVP-E20 Mi4INTENANCE S C H E D U L E

C: 0 -4 4J a U - -4 P: 't! U -4 - U a, a cn

B a z

d z

Jan 12/02 Page 9 . 3 - 5

C 0 -4 4J la- u m -4 H '44 U -4 - 0 Q) a V1


M ~ L I N T E N A N C E SCHEDULE

Page 9.3-6 Jan 12/02 R



> 5. - -

-I+ -4 -I+ a, U

C U k U k C C k C 4J tr -4

d k m u a u a, m -4 -4 m a, -4 a, -4 a, c a, c -4 a r l - ~ C O C 4J a 4J

C d a u m o c a a 4~ k O k O k a) C, O l k k

k m k a, C

g P t x P t m a a, m m X Vl Pc U S X B 0 W

d 3 i

r l N r n . 4 ' m U) P a o - l o r l N m m m m m m m rn m m w d ' d ' d '

Jan 12/02 R Page 9.3-7



Page 9.3-8 Jan 12/02 R

LET L 410 WP-E20


9.5 List of sealed items

S e r . No.

1

2

3

4

Component

"FIRE EXT." push-button =overs.

"EMERGENCY LANDING GEAR AND FLAP CONTROL" manual valve.

Emergency static pressure m d total pressure instrument supply valve.

Maximum contingency power stop.

Location

pilot's cockpit.

In pilotls cockpit - right control panel.

In pilot's cockpit - left control panel.

pilot s cockpit.

Page 9.5-1

LET L 410 WP-E2O



- Page 9.5-2 Aug 31/95

LET L 410 UVP-E2O


I 9.6. List of adjustable items whose adjustment durins service is

I I prohibited

All instruments and major components on engines, propellers

fuel system, hydraulic system and electric and avionic

equipment which are provided with the seal of the

manufacturer may be adjusted only by the representatives of - - - - - - - -

the manufacturer or persons authorised for the adjustment-by

the manufacturer.

I NOTE: Permitted adjustment of the LUN 6590.05-8 control

I I unit see MM of the M 601 E or M 601 E-21 engine,

I para 73.21.00, page 501.

The following components of the M 601 E or M 601 E-21 engine

may be replaced only by the persons trained by the

manufacturer:

- Compressor-relief- valve and fue-l metering nozzles - Accessory drive shaft packings - Engine controls - LUN 3280-8 automatic feathering pressure switch

- Fire seals - LUN 1540-8 torque transducer/transmitter

- LUN 1539.02-8 torque indicator

- LUN 1476-8 torque limiter transducer/transmitter

Page 9.6-1

LET L 410 UVP-E2O



- Page 9.6-2 Aug 31/95


JXE%INTENANCE SCHEDULE

9.7. Operation of instruments and major components

Comments on the following tabelar listing:

9.7.1. Data are given in flight hours and years except for such

cases where another value marking is stated (e.g. number

of landings). When the values are given in flight hours

and years or in the number of landings, always such value

is valid which elapses earlier.

9.7.2. The beginning of the operation time of the aircraft

including the instruments and major components is taken

from the date of acceptance by the customer stated in the

aircraft log book, exept for

- the PPL (8) fire extinguisher whose TBO is counted since its production date (or testing)

- fuel rubber tanks (chapter 028, item No. 27-30) whose

service life is counted since its date of manufacture.

9.7.3. The dash in the column llTBO, hours, yearsv1 means that

these items are not subject to overhaul.

9.7.4. The dash in the column llService life hours-yearsf1 means

that the service life is not limited by flight hours or

years.

9.7.5. Data given in the column llTBO1' mean the time till the 1st

overhaul and also the intervals (times) between further

overhau1s.A tolerance of + 5 % is applicable to the indi-

cated vdlues ,except for the TBO of the engines aid propellers.

9.7.6. The changes of the TBOs and of the service lives of

instruments and major components of CR manufacture

are given by bulletins.

Jan 12/02 Page 9.7-1


JXAINTENANCE SCHEDULE

9 . 7 . 7 . For products of a limited TBO (or service life) are the

work procedures for their replacement given in the

respective chapter of the Maintenance Manual.

9.7.8. The operation of instruments and major components as per

their technical condition is given in the table by the

abbreviation Iton conditionn. The serviceability is

evaluated either in the aircraft or in the laboratory (see

Chapter 4) according to the technical data given in'the

Maintenace Manual.

In case of not complying with the technical requirements,

the instrument or major component is dispatched for the

repair.

1 9 . 7 . 9 . Hose service life for hose manufactured of PND material

given in Chapter 000 of Maintenance Schedule is increased

to 15 years since the date of hose manufacture,of which 10

years of operation in the airplane. Hose service life is

given by time since the date of hose manufacture or by time

of operation in the airplane depend on which time expires

first.

The hoses must not be stored by the operator for more than

2 years. If their storage life is exceeded the hose must

be rejected.

Example of hose markinq

11.93 125 X.93

Hose manufacture Certificate Date of date number installation

in the aircraft

Page 9.7-2 Jan 12/02



Maximum storability of the hoses manufactured of AE 303 material with fittings is 2 years - calculated from the date of production of the hoses material (a date is given on a hose). The hoses with fittings must be installed on the aircraft not later than the storability is expired and they must be used in operation for max.5 years without consideration the storability is used or is not used. If the hoses are installed later than after 2 years then the operational period is shortened by the period of delay of the installation on the aircraft. The operational period is calculated from the date of hoses installation on the aircraft.

The AEROQUIP teflon hoses with unlimited service life can be used on the airplane, ie. dashes are mentioned in the section 000 of this MS and in columns TBO-Hours-Yrs and " Service life-Hours-Yrs " (see item 9.7.3 and 9 . 7 . 4 ) .

Comme,nts on the data in tables

Validity is given-from the series

Pcs set

from the prod. No. of aircraft

number of pcs for 1 aircraft number of sets

e.g. from the 18th series

The maintenance of instruments 'Ion conditionn is given in the Maintenance Schedula - periodic maintenace.

The service life of the instrument marked Iton ~ondition'~ expires in case of such a defect, repair of which is not economical any more.

If another data for maintenance, TBO and service life for products of CR are given in this Maintenan~e~Schedule than in the product's certificate, the data 'stated in this Maintenance Schedule are valid.

Jan 12/02 Page 9.7-3



- a, 'ti 4 Gl

4J 'ti (d k U k -4 A

Jan 12/02 Page 9.7-4



N U) m m U) LO F P 0 rl 0 rl rl rl rl rl m k m m k m m k m m k m

0 0 0 0

Jan 12/02 Page 9.7-5


MZLINTENANCE SCHEDULE

Jan 12/02 Page 9.7-6



Jan 12/02 Page 9.7-7

7-8

LETECKE ZAVODY a.s . L 410 WP-E2O

JYUXINTENANCE SCHEDULE

u7 10 CV I0 d'd ' rl I+

(U o r k r U3 rl k m o m d ' d ' 0 u7 m

tsl m - m m . .

,-&v)- - ~. ~ ~ ~

a x r x + N a a

x trl

m ID d 'd '

CV 0 U 3 d k d 'd ' 0 J . . a ^ m u a x r

X m m e I

Jan 12/02

-

No.

Name of Unit

z)

hoses of

hydraulic

system

(continued)

Effect.

Type /Dwg. No./

Time Limits

TBO

Hours

Service Life

Yrs



u r( d' 0 b N Kl LO U) m a U) U) m U) d' U) rl rl m e r( 4 m rl

b b m 0 b b r. b k u k m iD rl k l o k l n m k u l o u l o m d ' d ' o m o m m o m

J

Page 9.7-10

-

Jan 12/02

LETECKE ZAVODY a . s . L 4 1 0 UVP-E20

M A I N T E N A N C E SCHEDULE

m S ~n co N m U) COO- rl rl

rl In m * * k b k P U ) m o I n o m W d J _ u7 In

b b m k m m o m

4J 0 al ccl ccl W

Jan 1 2 / 0 2 Page 9.7-11



m n o x P . . ~r a ~ r r n n x * n ~r LC P * x x x 0 m Pr4 P P 0r l l

X 0

x cn

rl- ' r i rl rlrl rl

Page 9.7-12 Jan 12/02

Name of Unit

c) hoses of

hydraulic

system

(continued)

Effect.

Type /Dwg. No./

25HF B 463 979 N

(25HF L 410 WP.

.4670-244)

(without weather

radar installa-

tion)

Time Limits

TBO

Hours

Yrs

Service Life

Hours

Yrs



0 I i-i

Z 0 al m o

rl- m d'o u m . 4 * d m 0

I k - - -

m G a c X 0 ErQa 0

X r- Fr Er h rl Fr Er Er u

X .rl a -4 X X X N d ' x X X a d ' m 3 k u m V) m m m N N N d ' N U N N m u . m m e -

Page 9.7-14 Jan 12/02

LETECKB ZAVODY a . s . L 410 UVP-E20

-1NTENANCE SCHEDULE

Jan 12/02 Page 9.7-15



Page 9.7-16 Jan 12/02



Jan 12/02 Page 9.7-17

7-18

LETECKE ZAVODY a.s . L 410 UVP-E20


Jan 12/02



P P m k m m o m

Jan 12/02 Page 9.7-19


lXLRINTENANCE SCHEDULE

Page 9.7-20 Jan 12/02



Jan 12/02 Page 9.7-21

LETECKE ZAVODY a .s . L 410 UVP-E20


Page 9.7-22 Jan 12/02


Okla aa U I a.rl

Jan 12/02 R Page 9.7-23



Page 9.7-24 Jan 12/02 R

LETECKE ZAVODY a.s. L 4 1 0 W P - E 2 0


Jan 1 2 / 0 2 Page 9 . 7 - 2 5



5 . d a,

rn E: a, 0 E: E 0 PC 2 0 Ptk k U a -4 W E

Paue 9.7-26 Jan 12/02 R



Err x W

3u W

0 I

w' r'l rl m N cn rl

Q) C, C U

k n U-4 c, a a - d C x -4 aa, 0 5 o Q) &TI A C

3 > k

m 0 TI 0 U a U Q ) rl C a ac , .ria o PI -rl m ~ l k LI o c, C A 0 4 k k

0.4 U U C U Q) U O Q ) 0 -4 C 4'44 O k U r, H 0 -4 h h h

3 - a n u a

k - Q) a S Q) -4 rl Q) rl U a Ul c, C m a C k -4 E-r

'44 Err -d X u

Jan 12/02 Page 9.7-27

LETECKE ZAVODY a.s. L 4 1 0 WP-E2O


C T I tn

.rl k 0

k m - A 0) I a O W C 0 - r l 3 Id-

m $ E

-rl

$ . rl w

Page 9 .7 -28 J a n 1 2 / 0 2

0) ccr -4 GI

0) U

-rl

L 0) M

G I -

0 m w



k 0

rl 0

P P d'd' rl rl CV CV

z z 5 3 4 GI

a, a, I I

m d' a, 0 0

1 . . 0 m m U) d'd' d' P P CV CV CV

k 0 a, I

0 0 m m d'd' CV CV

z z 3 3 4 GI

Jan 12/02 Page 9.7-29



c, 0 a ccl ccl 4 1

ccl 0

fd 0 eel -4 c, C

,-I r( fd

a fd -4 k Cc, c,h h C, k Q I kC, Q f d C 04: a,a, Q d 7 U 0 4Jcc-l -4 a, A X O Cfd Clk V] W U I H t n

1 Page 9.7-30 Jan 12/02

LETECKE ZAVODY a . s . L 4 1 0 UVP-E20

I?/LAINTENANCE S C H E D U L E

I e l I

Jan 12/02 R Page 9.7-31

Sh

ap

ter

N

o.

-

22

.

23

.

24

.

25

.

26.

27

.

28

.

Na

me

o

f U

ni

t

Ef

fe

ct

. T

yp

e /D

wg.

N

o./

N

In

st

ru

me

nt

s u

sed

a

lso

in

oth

er

ch

ap

ters

:

Ci

rc

ui

t b

rea

ke

rs

Co

nt

ac

to

r

Co

nt

ac

to

r

Co

nt

ac

to

r

Co

nt

ac

to

r

Co

nt

ac

to

r

Co

nt

ac

to

r

AZ

RG

K

+ A

ZR

rKD

1

03

DO

D

or

I'KD

1

03

OD

L

FKD

5

01

DO

D

rKD

5

11

DO

D

rKS

2

01

DO

D

rKS

4

01

DO

D

rKD

1

33

DO

D

or

I'K

D

13

3 O

DL

Tim

e L

im

it

s

TB

O

Ho

urs

Y

rs

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rv

ic

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ife

Ho

ur

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in

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S

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S

CI

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Jan 12/02 R Page 9.7-33



rl f'a m

Page 9.7-34 Jan 12/02 R

No.

-

1.

2.

3.

4.

Name of Unit

Fire protection

Fire extinguisher

bottle

a) Bottle

b) Discharge head

c) Pressure

gauge

d) Pyrocartridge

Fire extinguisher

Smoke detector

Pregsure gauge

Effect. Type /Dwg. No./

PPL (8)

(Dwg. No.

B 067 300 N)

72-6600-20

B 067 308 N

MA16K(from 19th

series modify as

per Dwg.

No. B 580 758 N)

Time Limits

TBO

Hours Yrs

condition

- -

- -

on

condition

I on

condition

Service

Hours

on

conditi

20 000

-

on -

Life

Yrs

condition

Origin

CR

CR

CR

CR

CIS

CIS

G U-l W

Page 9.7-36

LETECKE ZAVODY a .s . L 410 W P - E 2 0


4J 4J rl rl r l a rl m m ri a rl rl ri rl

m rl rl m

nj I l P l r n

H cn PI m c n a

k 0 4J r d k -4 0 U 4J C U

a 5 a k C 4 J -4 C a lcl rda

h

U

Jan 12/02



I0 N I0 TP ( V a l ( V m 0 0 0 0

Jan 12/02 Page 9.7-37


4J G4J I O U 40rCr

Page 9.7-38 Jan 12/02 R


M2lINTENANCE S C H E D U L E

b - 0 r l w o w z Tr

u C1 -ZU3 z

Jan 12/02 Page 9.7-39



Page 9.7-40 Jan 12/02 R

Chapter No.

-

1.

2.

3.

4.

5.

6.

7.

8.

-

Name of Unit

Fuel

Pressure switch

Wing tip tank

(if installed)

Three-pointer

indicator

Fuel gauge

indicator

Wing tip tank

fuel gauge

Fuel gauge

transmitter

Fuel gauge

transmitter

Fuel gauge

transmitter


0.012

K

LUN 1492.01-8

B 562 600 L,P

LUN 1538.XX-8

LUN 1634.01-8

LUN 1674-8

LUN 1635-8

LUN 1636.01-8

LUN 1637-8

Time Limits

TBO

Hours Yrs

Service Life

Hours

20 000

on

conditi

10 000

8 000

6 000

10 000

10 000

10 000

Yrs



a, u m -d k

5 z 0 a, X (I]

Page 9.7-42 Jan 12/02 R



? 5 $ rl rl rl -4 -4 -4

k '4.4 w w k C C C a, rl 0

2 k k C, X X X a) C, 5 s rl C C C

c, 4J c, -4 (d a (d (U -4 > (d

a, a, a, w c, c, c, rl 0 k k k k k k C I I I rl r l a , rl a, r l a , ? r l 5 C C C 3 a , ?

5 0 a, C

0 0 0 5 0 5 0 z Z Z F F 0 F 0 F 0 F a a , S 5 C

P w m 0 rl N m d' rl rl rl N N N N N

Jan 12/02 R Page 9.7-43

7-44


8 8 8 E U

Jan 12/02 R

M2%INTENANCE SCHEDULE

Jan 12/02 R Page 9 .7 -45

7-46


P&%INTENANCE SCHEDULE

Jan 12/02 R


Jan 12/02 R Page 9.7-47



Page 9.7-48 Jan 12/02 R

L 410 UVP-E20 MAINTENANCE SCHEDULE

rl rl -4 rl k rd

5 W C -4 C a,

0 c, D

' H O a, -4 -4 a, c, a, k c , C c, 3 -2 k 3 U 0 0 3 m a, m rn m m C c, C m m a,

U C a,C 3 0 Q) rd k 0 k k k PI U rn 0 PI c, PI

b a) cn 0 4 N r'l rl rl rl rl N CV N N

Jan 12/02 R Page 9.7-49


N r l 0

m m m C n r l G l r l r l o r l N m o m m

Jan 12/02 R Page 9.7-51



P a g e 9.7-52 Jan 12/02 R


MJlINTENANCE SCHEDULE

cll

8 H U

rl - a 0

- o \ o co o m CI

pzlo co w

0 rl * ( V

m mco FU) m S LO & S O I

b n w n m w m m -a cll

m .", -4

Jan 12/02 R Page 9.7-53

C C C F: C 0- 0- 0- 0 0 -4 -4 -4 -4 -4

U +J C, 4J 4J 4J .4 -4 -4 -4 -4 -4

?! o a a a a a I

C C C G F: E O X I- o C 0 C 0 C 0 C 0 C 0

(V cll 0 0 0 U 0 U 0 U 0 0



Page 9.7-54 Jan 12/02 R



N f'l Ln CJ

Jan 12/02 R Page 9.7-55



Page 9.7-56 Jan 12/02 R



Jan 12/02 R Page 9.7-57

7-58



-4 -4 u 0 4J 0 -4

a g a , 0

k k C a 0 4J 4J C u m

0 C 0 Pa

U C C 0 U

- - - - - - - - - - a-rf 0 - - - - - -

- - - - - -

- - - - -

a-rf m 34J E: LI m - r l

Jan 12/02



C U - cr a -d a,

$ z rd

a, c, k m 1 C m -d m

@ + I k -4 PI-

Jan 12/02 R Page 9.7-59



Page 9.7-60 Jan 12/02 R

ccl W

LETECKE ZAVODY ass. L 410 UVP-E20


- rl

h h rl z 3 Z I

P CV I . m - 0 0

l-i W m o d - 0 0 --ZUJ - Z

UJ P z e w m 0 h . .

Jan 12/02 R Page 9.7-61



F b X F X F Dl C k k C C

z .,+ -rlx a) - rl a) 0 -rl -4 rl CI]

rl 4~ 4~ a - a - a o a a) a F d 4J d 4J F: F C F C O k C F a) b a) c m -rl : 'g m a)

m a, mG a) rd a) d rl

G C m .rl -4 E rl rl rl rl 4 m a 3 -4 I rl 4~ m 4~ m k LI

(w a k E: k c c k C L I G k O a)k a): a) rl s a m a) rd -4 m -rl m -rl m m m Q) a) o I=& c k m a) g: oc, 0 a) (IIU H CI H 4~ z F z r r m Z F a m

Page 9.7-62 Jan 12/02 R

Zhapter

032

-

No.

Name of Unit

Main landing

gear wheel

Brake

Nose landing gear

uheel

4ain landing

year tyre

Nose landing

gear tyre


720x310

model 3 TUBELESS

or

model 4 TUBELESS

or

29~11.0-10/11

OT01-1

GOODYEAR

550x225

model 4 TUBELESS

or

9 ' 00-6/906~06-1

GOODYEAR

Time Limits

Hours I Serv

ice Life

Hours

9 000

landgs

- -

Yrs

Origin

CR

CR

USA

CR

USA


M2%INTENANCE SCHEDULE

Page 9.7-64 J a n 12/02 R



ccl W I

k c , k

Jan 12/02 R Page 9.7-65



Page 9.7-66 Jan 12/02


Jan 12/02 Page 9.7-67

No.

-

1.

2.

3.

4.

5.

6.

7.

-

Name of Unit

~irs~eed

indicator

Airspeed

indicator

Vertical speed

indicator

am' pressure

head

Static pressure

head

Pitot tube

Speed signallizer

Effect.

LUN 1108.XX-8

LUN 1~113.XX-8

LUN lb40.XX

LUN 1155-7

LUN 1156-7

LUN 1157-7

LUN 1173.XX-8

I

Time Limits

TB

O

Hours

-

Yrs

Service Life

Hours

Yrs

LETECKE ZAVODY a - s . L 4 1 0 UVP-E20

PJlAINTENANCE S C H E D U L E

a, U (I]

-rl k $ s k 0 a, 32 cn

Jan 12/02 Page 9.7-69


k a Cl

U 4J -4 b'-4 4J C R a-rl m C S C b'a a rd rl k.' z m u h

u

Page 9.7-70 Jan 1 2 / 0 2 R

I-'

4

I-'

Transponder

sydtem

(is installed)

b) ~ncoding

Altimeter

tray

I I

Transponder

system

(if installed)

I

b)Encoding

I altimeter

I tray

I )Lighting

2

sets

2 2 2 2

1

set

1

1

1

1

I

Time Limits

Origin

US

A

US

A

US

A

US

A

US

A

US

A

US

A

US

A

US

A

US

A

LETECKE ZAVODY a.s . L 410 UVP-E2O


w' m 0

Jan 12/02 R

a, 'ti - d d

a, U -d

t a, cn

LETECKE ZAVODY a s s . L 4 1 0 WP-E20

M2XINTENANCE S C H E D U L E

Jan 12/02 R Page 9.7-73

7-74



c, r i a , rl N N

cn

Jan 12/02 R


a C a, 0

rlrl u a r l 4 c a 3 Oc, a -4 ul

Jan 12/02 R Page 9.7-75



Jan 12/02 R


MSLINTENANCE SCHEDULE

Jan 12/02 R Page 9.7-77



C Q) a\ a h O) x 4 0 4

m Id O ) ? U 44J m Q a G Id k-d +J a k aw 0 a-d PC a -

Page 9.7-78 Jan 12/02 R


0 z U)

k ru a) El] rl

0 CO 4 EU) Ln 0 0

to I

d' 0

CV cn d'

El] rl

b z - 5

0 cll

Jan 12/02 Page 9.7-79

-

No.

-

1.

1.

2.

3.

-

Name of Unit

Power plant

Engine (includinc

major components

inGtalled on

engine )

Enqine controls

Genkrator speed

derivative

element

1ntGgrated

eleotronic

limiter unit

Ambient air

temperature

transmitter

Effect .

Type /Dwg. No./

LUN 5223-8

LUN 5260.XX

P-5 (7:)

Time Limits

TBO

Hours

2 000

or

2 250

cycles

- - -

Yrs

5 - - -

Service Life

Hours

6 000

or

6 750

cycles

9 000

5 000

8 000

Yrs

10

10

-

LETECKE ZAVODY a.s. L 4 1 0 WP-E20


J a n 1 2 / 0 2 R Page 9 .7 -81



Page 9.7-82 Jan 12/02 R

LET L 410 W P - E 2 0


9.9. Statistics and elaboration of operation defects influencinq

the operational safety

The given service life of individual airframe parts which

follows the chapter 2 , is estimated for the presumed

utilization of the aircraft from the operation given by the

following parameters:

I Average flight T = 60 minutes 1 The life is analyzed and tested in laboratories for four

typical flights I, 11, 111, IV, the first three being

without the wing tip tank, the flight IV. is with the wing

tip tank.

Flight profile

Flight time (min)

Flight probability

G .......p ay load max.

PL . max .

Pay load

ti

PL . max .

0 . 8 G PL . max .

0 . 8 G PL . max .

The determined life for the above

operation is given in the chapter 2.

Flight altitude

Runway ratio

zoncrete grass

mentioned average

The life is given

here also for permanent flights IV., (with wing tip tanks).

The diagram of the dependance of the service life on the

percentage of flights with WTT is also given. - Aug 31/95 Page 9.9-1

LET L 410 WP-E20


Average data for the flight IV.:

I Flight altitude 1 1.2 km I Flight time

The given lives in the chepter 2 . are valid for the

average operation parameters and the given routine and

periodic maintenance inclucing the inspection of the

aircraft. With significant deviations from the presumed

operation, other defects and failures may occur on the main

structural parts of the airframe which have not been found

during fatigue tests in the laboratory. The defects and

failures influencing the safety level of the flight must be

statistically followed during periodic maintenance,

inspection of the aircraft and unscheduled inspections.

The increasing number of defects with some parts due to the

increasing number of flights indicates reaching their life

t time. Such parts must be preventatively in advance replaced

l or repaired.

I The statistics of defects is recorded in a form and I submitted to manufacturer of the aircraft for his opinion. I I The originating defects may be considered from the I following viewpoints

200 min. 1

I - defects of common nature (mechanical wear and damage) I occuring in the average like with other types of I I aircraft. Such defects do not influence the life and are

I not noted in statistics.

1 Page 9 . 9 - 2

LET L 410 UVP-E20


- defects due to variable loads during operation (loosening of rivetted joints, cracks in subsidiary fittings).

Such defects found especially during the inspection of

the aircraft are removed by tightening the rivets,

replacement of fittings ets., as far as their statistical

number is acceptable and do not increase with the

increasing - - - - hours flown. They are recorded in statistics - - - - - - - - - - - - - - - - - - -

only if their number is increasing considerably.

- defects due to the variable loads in operation

influencing the life (e.g. cracks in engine mount in main

structural parts of the aircraft, fuselage and tail unit

ets.) Such cases are solved by a repair or replacing the

part and are recorded in statistics.

The filled-in statistical forms are sent once a half-year

to the manufacturer of the aircraft with a request for an

advice how to solve the defects of a mass occurrence. - - - - - - - - - - - - - - - - - - - - - - - - - - -

Example of statistical form for recording the defects of

the airframe is enclosed in this supplement.

Notes for filling-in the defect statistics

- number of observed aircraft in the given period at a I

single user

- only major component are mentioned: fuselage,

wing,

engine mount, - landing-geaF attschnent -f ittings -

horizontal tail sufraces,

aircraft controls,

wing flaps.

- only defects of a more serious nature are recorded which

might influence the level of flight safety. -

Page 9.9-3

LET L 410 UVP-E20


In the column - Measure - one writes e.g. replacement of

part, repair as per section 5, repair on the suggestion of

the user, repair on agreement with the producer, repair by

the manufacturer etc. Here also one states the proposal for

the observation in the further operation and for the

measure concerning the whole fleet of aircraft at the

respective operator. - - - - - - -

- in the column - Defect type No. - one notes the numerical symbol selected by the user for a certain defect type. The

user marks then the same defect in any further report by

the identical number.

- in the column - Defect found during inspection - one notes :

routine maintenance

periodic maintenance

inspection of aircraft

etc.- - - - - - - - - - - - - ~

I - Page 9.9-4 Aug 31/95

LET L 410 UVP-E2O


31/95 Page 9 . 9 - 5

LET L 410 WP-E20

M2kINTENANCE SCHEDULE


- Page 9.9-6

LET L 410 UVP-E20


I 1 9.10. Special airframe inspections.

9.10.1. General

The critical areas of the airframe were found by fatigue

and static strength tests. These areas must be very

carefully observed during 4 800 hrs inspections and

possible inspections made by the aircraft manufacturer - - - - - - - -

or by the representative b f supervisory authority; - - -

The critical areas are examined with a magnifier of a

minimum magnification 5 : l . During the inspection these

areas should be examined on disassembled parts of the

aircraft structure. The found defects and cracks are

repaired in accordance with the instructions given in

this Maintenance Schedule. Repair of cracks and larger

defects, which is not mentioned in this Schedule and in

the relevant documents, is solved as follows:

- in case- oc a- smaller - extent concerning the secondary_ structural elements of the airframe the repair is done

according to the practice of the user with the

condition of maintaining the same strength without the

approval of the manufacturer.

- in case of fatigue defects and mechanical damage on

primary structural elements of the airframe the repair

must be consulted with the aircraft manufacturer.

9.10.2. List of critical areas accordinq to structural sroups

Winq - - - - - - - - - - - - - - - - -

- - - - - - - - -

Areas of the lower cap of the fore spar. Skin cross

splices on the lower wing side.

May 15/98 Page 9.10-1

LET L 410 UVP-E20


Partition of the fore spar caps on the lower side between

the ribs No. 10-11.

Web of the aft spar between ribs No. 22-25. Wing to

fuselage rear attachment fitting in the area of holes for

I screws M 7 (fixing of the fittings to the lower cap of

the aft spar). Lower cap of the aft spar at the rib

Skin around the inspection holes on the lower wing side.

Holes in attach fittings for the bolts of wing-fuselage

connection (check for ovality, after 14 000 flight

hours ) .

Fuselaqe

Lower cap of landing gear spars on frames No. 12 and 14.

Holes for bolts of wing-to-fuselage attachment fittings

(check for ovality after 14 000 flight hours). - - - - - - -

Attachment f-itt-ings - for the - tai-1 unit at frames

No. 25-26.

Tail unit

Suspensions of stabilizer.

Suspensions of tail fin.

Connection of longitudinal stringers with cross ribs

between the spars of the stabilizer (cracks in the skin).

Caps of the fore stabilizer spar in the place of

stabilizer attachment fittings. Suspension bushings of

tail unit (corrosion, wear)-.- - - - - - - - - - - - - - - -

- - - - - - - - - - - - - -

- Page 9.10-2 May 15/98

LET L 410 WP-E20

JXAINTENANCE S C H E D U L E

Repair of common defects without the manufacturer's consent

In order to determine the possibility and way of repair

examine carefully the damage extent by inspecting the

structure, some times even after a partial removal of the

skin rivets.

The process for defect removal of skins and airframe parts

is given in the Maintenance manual (subjection 020.20.00)

where also the process for repair of damaged parts is

described. In this Maintenance Manual are also mentioned

permissible deformations which may be left in operation

without repairs, thickness of individual itens, drawings of

structural connections, process for finding out loosened

rivets and further technical requirements for repair.

If you do not find the repair process in the Maintenance

manual or in this supplement, request the manufacturer for

the way of repair which secures you maintaining the

requirement of the safety level of flight.

The defects be divided the following groups :

- small defects which need not be repaired, like local

dents of the skin, crazing in the skin not exceeding the

depth of cladding, appearance defects of paint,

upholstery etc.

- defects which may be repaired according to design rules

and work procedures for repair of assemblies as per the

Maintenance manual

- defects with the fault of the primary structural elements (deformation of the wing spar or stabilizer spar,

deformation of ribs, wing, fuselage frames etc.). Such

repairs may be carried out only by a specialized repair

shop or by the manufacturer. - Aug 31/95 Page 9.11-1

LET L 410 UVP-E20

-1NTENANCE SCHEDULE

Maintaining of the conditions of the static and fatigue

strength guarantees the authorized repair shop which may

ask the manufacturer for approving it.

- defects of such extent that the repair is either

impossibble or so costly that it is better to replace the

damaged item for a new one either by the manufacturer or

authorized repair shop.

- Page 9.11-2 Aug 31/95

LET L 410 UVP-E20

MJiINTENANCE SCHEDULE

9.12. Replacement of details

9.12.1. General

In order to secure the routine maintenance, the

manufacturer supplies spare parts for the aircraft 1:1

and a set of spare parts for instruments and major

components. It is possible also separately order sets of

spare parts and materials 1:5 supplied with every fifth

aircraft (or in other way as per contract). On the

request of the customer the scope of the set of spare

parts may be enlarged. The work procedures for the use of

spare parts and possible supplementary operations are

given in the Maintenance Manual of the L 410 UVP-E20

aeroplane.

9.12.2. Process of spare parts procurement

During the operation of aircraft, excepting cases when a

part from the set of spare parts may be used for the

repair , secure the damaged detail, instrument or

assembly at the manufacturer. When doing so proceed as

follows.

9.12.2.1. Identification of detail

The equipped aircraft, structural units of the

aircraft, individual details, elements, instruments and

assemblies are provided with identifications (drwg.

No., standard, other marking etc.) State such

identificators in the spare parts order. The

identificators you may find by means:

Page 9.12-1

LET L 410 UVP-E20


- Illustrated Parts Cataloque

This Catalogue is meant as aid for ordering spare

parts of the aircraft. Only the removable parts of

the airframe are given in detailed drawings in the

Catalogue. The Illustrated Parts Catalogue for the

L 410 UVP-E20 aeroplane does not form a part of the - - - - - - - -

- - - - - - - - - ~

accompanying documentation supplied with every

aircraft.The customer may order it at the

manufacturer.

- Album of production, operation and repair tolerances

The album of production, operation and repair

tolerances is meant for the attendance of the

L 410 WP-E aeroplane in the course of periodic

maintenance and inspection. ~eside the data on the

correct dimensions and alignment during the

aircraft1 s operatian, - are - in - the columri, "drawing

numbern given the identifiers for the respective

component or standard parts. With some assembly

groups are in the column "Note1' given the drawing

numbers of repair drawings. All identifiers may be

used for ordering. This album does not form a part of

the accompanying documentation supplied with every

aircraft. The customer may it order at the

manufacturer.

- Inquiry on the service qroup of manufacturer - - - - - - - - - - - - -

- - - - - - - - - - - - - - - ~ ~

In the framework of the advisory activity at the

customer (service centre) one may exceptionaly make

an inquiry for the identification of the required

part.

- I I Page 9.12-2 Aug 31/95

LET L 410 UVP-E20


9.12.2.2. ~rderinq of spare parts

After the identification proper of the respective

part (spare part) order as follows. State in the

order:

- identifier - name of ordered part - pieces of ordered parts. With planned spare parts

give also the partial deliveries in individual

quarters of the year.

- serial number of aircraft for which the spare parts are ordered (does not concern the standardized

parts )

- Aug 31/95 Page 9.12-3

LET L 410 UVP-E20


I - I Page 9.12-4


Aug 31/95