/ms_r05 by AirTech Book

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 essential that you do your part. Comments, corrections regarding this manual are welcomed and should be sent to: Documentation Department LET, a.s. 686 04 Kunovice Czech Republic EUROPE or fax us to: Documentation Department +4ZO 632 61 352 or send us e-mail to: dnts@let.cz

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.. . ,

LET L 410 UVP-E20 -1NTENANCE SCHEDULE RECORD OF TEMPORARY REVISIONS

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CONTENTS Page 1-1

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 9.9. Statistics and elaboration of operation defects influencing the operational safety 9.10.Special airframe inspections ................. 9.11.Repair of common defects without the

manufacturer's consent ...................... 9.12.Replacement of details ...................... 10. APPENDIXES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

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LET L 410 UVP-E20 MAINTENANCE S C H E D U L E

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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LET L 410 UVP-E20 MAINTENANCE SCHEDULE 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

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LET L 410 UVP-E20

MAINTENANCE

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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

LETECKE ZAVODY a.s. L 410 UVP-E2O MAINTENANCE S C H E D U L E 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 book,chapter V1,Aircraft into the aircraft log operational records,into the Remarks column,must be entered,reading : "WTT + ' I . 1.1.3. Numberinq

scheme of the Maintenance Cross-reference to Other Publications

Schedule

and

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.

Jan 12/02

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LETECKE ZAVODY a.s. L 410 UVP-E20 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

Engine MM

Propeller MM

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

Page

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Jan 12/02

LETECKE ZAVODY a.s. L 410 UVP-E20

MAINTENANCE

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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 revisions11is 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 revisions11cancelled 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

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LETECKE ZAVODY a.s. L 410 UVP-E20 M A I N T E N A N C E SCHEDULE

w/p

Work Procedure

Left-Hand (Port)

Right-Hand (Starboard)

Rud

Rudder

Elev

Elevator

Maintenance Schedule

IELU

Integrated Electronic Limiter Unit

L/G

Landing Gear

gas generator speed

propeller speed

indicated airspeed

n V

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1-8

Jan 12/02 R

LETECKE ZAVODY a.s. L 410 W P - E 2 0 MAINTENANCE S C H E D U L E

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

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LETECKE ZAVODY a - s . L 410 UVP-E20 MAINTENANCE SCHEDULE

1.2.1.6.

For

the

actual

danger

areas

around

the a i r c r a f t with

e n g i n e s r u n n i n g see f o l l o w i n g d r a w i n g : a ) with engines

b ) with engines

a t i d l e power

a t max. T/O power

When i n s p e c t i n g t h e

1.2.1.7.

powerplants a f t e r t h e i r shutting-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 c a u s e d by c o n t a c t w i t h

them. P o r t a b l e e l e c t r i c lamps, u s e d d u r i n g t h e inspection of &h_e

1.2.1.8. . -

aircraft, cages

.must be

and must

not

without d e f e c t , spark

must have

when s w i t c h e d

protective

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.

Page 1-10

A i r c r a f t max b e s e r v i c e d t o wind s p e e d of 1 5 m / s .

Jan 12/02 R

LET L 410 W P - E 2 0 MAINTENANCE SCHEDULE

Safety principles for work on elevated surfaces

1.2.2. 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 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).

be done wearing

safety

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 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 exceed 5 m/s.

be lifted if the wind

the

jacks, it is

velocity does not

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 MAINTENANCE SCHEDULE

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 observe following rules:

substance. When handling it

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.

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LET L 410 UVP-E20 MAINTENANCE SCHEDULE

Handling the oil system is permitted only after the pressure to the level of atmospheric pressure and oil temperature drops below +60째c. 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 b e d o n e 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 c o u r s e -and have practica-lhands-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 beginning -of _the-fillin-g, -

equipment -

ready

before

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.

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1.2.8.

Safety

1.2.8.1.

SCHEDULE

principles for use of flammable liquids

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_leliquid f-orcleaning 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. - -

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LET L 410 UVP-E2O MAINTENANCE SCHEDULE

2 AIRWORTHINESS -

SE<3TION

LIMITATION

TIME

LIMITS/MAINTENANCE

CHECKS

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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 replacements

systems liable to

compulsory

Table of service life of the airframe and its systems

Ser , No.

Name

Marking

Service Life ( LB 1

Rear landing gear spar

Left rear cable

6 200 hr

Right rear cable

6 200 hr

Central right cable

6 200 hr

Central left cable

Front cable

May 15/98

13 000 flight

cycles

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LET L 410 W P - E 2 0 PJLAINTENANCE SCHEDULE

Ser No.

Name

Marking

Aileron fabric skin

B 025 641 P ribs No. 3-14

Aileron fabric skin

B 025 641 L ribs No. 3-14

Elevator fabric skin

B 533 201 P ribs No. 3-17

Elevator fabric skin

B 533 201 L ribs No. 3-17

Fabric skins of rudder

B 531 201 N ribs No. 3-17

Service Life

Fabric skin service life on condition

Notes to the table: 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.

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)

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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 f01 lowing flights (training flights) perform when airplane is filled with fuel

routine maintenance B

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.

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

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 defects shall be repaired only by a trained engineer. 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

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LET L 410 UVP-E20

MAINTENANCE Reference No.

SCHEDULE

Note

Scheduled Maintenance Check

Carry out the exterior inspection

FIG 3-1 INSPECT THE EXTERIOR (A) - beginning of inspection (11 Wingjsurface-,indications of fuel leakage, interceptors, rolling tabs; (2) Ailerons; (3) Interceptors, 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). -

Page 3-4

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May 15/98

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L 410 UVP-E20 M A I N T E N A N C E SCHEDULE

Reference No.

Scheduled Maintenance Check

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

Note

After the embarking of passengers.

Remove the blocking bolts from the (valid for emergency exits and put them into airplanes the pocket on the right side of the pilot's cockpit. with emergency door in pilot's cockpit and passenger cabin) 012.00.00.G

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.

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

Defecate the fuel tanks (15 minutes after refuelling)

Jul 15/99

Defecate the fuel cleaners

3nly before the first flight.

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

3nly in winter ;eason.

Page 3-5

LETECKE ZAVODY a.s. L 410 UVP-E20 MAINTENANCE SCHEDULE Reference No.

Scheduled Maintenance Check

Note

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

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

Install the storage battery.

Only if removed.

Check-the voltage of every battery separately. Connect the ground

power unit.

Disconnect the ground power unit from the airplane.

After starting the engine.

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.

Page 3-6

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L 410 W P - E 2 0 MAINTENANCE S C H E D U L E

Reference No.

Note

Scheduled Maintenance Check

Check the function of pilotage system. Check the air pressure in the pneumatic system. -

- -

Check or set the correct time on thelDo once in 2 days. aircraft clock. With mechanical clock wind i~ up. Check the operation of the BUR-1-2G flight recorder.

Carry out only if mounted on the aircraft.

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 weather radar. -

the

if removed;

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

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

J u l 15/99

Only

cary -out only in mounted on the aircraft.

LET L 410 UVP-E2O MAINTENANCE SCHEDULE Reference No.

Scheduled Maintenance Check

Note

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.

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

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

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 Readjust the levers of the flap control behind the oil cooler in the temperature drop engine nacelles. of the ambient air below +30°c and with the temperature rise above +30°c.

Check whether the seal of setting maximum contingency rating has not been damaged. 076.10.00.1 Adjust the switches of the (Engine MM, tic feathering on engines. technologic process 76.10.00.f)

Page 3-8

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

LET L 410 WP-E20 MAINTENANCE S C H E D U L E

Scheduled Maintenance Check

Note

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

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

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

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

Discharge system of the inner injection

Carry out at a temperature d r o ~ of the ambient air below +loOc. Clear away the preservation of the water injection system witk the temperature rise above +20째c and check the operation of the system.

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

Fill the tank of the water injection system with water.

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.

Scheduled Maintenance Check

Note

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.

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

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 Carry out only - covers of air inlet to engines in case when and generator the stoppage covers of exhausts time of the - covers on Pitot tube and blindings ' airplane till of sensors of static pressure the next cover of air inlet to the toilet. take-off will exceed 2 hours.

?round t h e airpLane wi-ththegrounding cable.

Page 3-10

J ~

Aug 31/95

LET L 410 UVP-E2O

MAINTENANCE

Reference No.

SCHEDULE

Note

Scheduled Maintenance Check

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

'arry out only in case if the stoppage time of 3ircraft till the next take-off is mticipated to zxceed -2 h o u r s .

case

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

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-stemsduring the flight. -

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

012.00.00.G (valid for aircraft with emergency door i-nthe cockpit and the passenger compartment ) -

May 15/98

Open the entry door. Set the airsteps.

Do after the stop of engines.

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,

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

Page 3-11

LET L 410 UVP-E20

MAINTENANCE Reference No.

SCHEDULE

Scheduled Maintenance Check

Note

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

Carry out only in case when the stoppage time of the aircraft till the next D 1 2 . 0 0 . 0 0 . J After concluding the works on the flight will (in effect 3ircraft remove the airsteps and put exceed 2 hours. it inside the aircraft. Close and for air=raft with lock the entry door. Close the door 2f the emergency exit and secure it lmergency inside by turning the bar. Check fioor in the seal of the emergency exit. zockpit)

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

Remove the deck batteries in order to store them.

Page 3-12

Carry out only in case of the aircraft stoppage for more than 12 hours and a temperature of ambient air below - 2 5 O ~ .

Aug 31/98

LET L 410 UVP-E20 M.AINTENANCE

Reference No.

SCHEDULE

Scheduled Maintenance Check

Note

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

025.00.00.B

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

026.20.00.C

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

029.12.00.A

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

032.40.01.G

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

033.50.03.A

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

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

Clean and disinfect the moulds of the oxygen masks.

Jary out as 3er crew s requirement.

1035.30.02.8

J u l 15/99

Page 3-13

LETECKE ZAVODY a.s. L 410 WP-E20 MAINTENANCE

SCHEDULE

MAINTENANCE C Reference No.

Scheduled Maintenance Check

Note

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.

Only with aircraft of carge version.

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.

Page 3-14

Jan 12/02

LET L 410 UVP-E20 MAINTENANCE SCHEDULE

Reference No.

Scheduled Maintenance Check

Note

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.

Aug 31/95

Page 3-15

LET L 410 UVP-E2O M.AINTENANCE SCHEDULE

Reference No.

Scheduled Maintenance Check

Note

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 position lights and check their operation. 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.

061.10.00.C Check the position of the shifting (MM - pro- carrier ring. peller)

Page 3-16

Aug 31/95

LETECKE ZAVODY a.s. L 410 UVP-E20

MAINTENANCE

SCHEDULE

Reference No.

Note

Scheduled Maintenance Check

Inspect the transfer rings.

361.10.00.G Zlean and c m - - - - nrface.propeller)

treat the propeller -

373.11.00.A Inspect the agregates and pipings ~f the fuel system below the engine (MM zowlings and the inlet channel. ongine 73.11.00.a)

:heck whether the seal of the maximum contingency rating ~f engine has not been damaged. 079.20.00.B Inspect the instruments and pipings 3f the oil syst-em. TMM-engine 79.20.00.a) -

079.30.00.B Check the oil amount in the tank by (engine MM means of the signalling of the minimum oil amount. W/P 79.50.00.d) Inspect the 8 LUN 7377-8 valves in the left side of engine nacelles.

Jan 12/02

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L 410 WP-E20 MAINTENANCE SCHEDULE Reference No.

Scheduled Maintenance Check

Note

Intentionally left blank.

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LET L 410 UVP-E20 MAINTENANCE SCHEDULE

4 P E R I O D I C

Aug 31/95

M A I N T E N A N C E

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)

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4.1. General 4.1.1.

The periodic maintenance consists of:

line check 1

is 10

check 2

check 3

check 4

Remark:

done periodically 1 days.

is done after every 300

after

every

30 flight hours.

is done after every 1 200 hours.

30 flight

is done after every 2 400 hours.

30 flight

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 to be done with every footnote (e.g. 2+ second check 2).

........,

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

Page

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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

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MAINTENANCE

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Name of Part/Unit Scheduled Maintenance Check

AIR

Frequency Note

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 nonreturn 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 Jul 15/99

Only in case mounted in the aircraft.

FI Page 4 - 5

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Reference No.

- -

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

Intentionally left blank.

Page 4-6

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LETECKE ZAVODY a.s. L 410 UVP-E20 MAINTENANCE SCHEDULE -

Reference No.

- -

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

AUTO FLIGHT

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

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

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

- adjustment of the torque.

rope drive

After testing mount it again into the aircraft.

Chapter Jan 12/02

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Name of Part/Unit Scheduled Maintenance Check

Frequency Note

~~~-~~

Intentionally left blank.

Chapter Page 4-8

Aug 31/95

LETECKE ZAVODY a.s. L 410 UVP-E20 SCHEDULE

MAINTENANCE Reference No.

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

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). 023.60.00.A

Check the static discharger.

023.60.00.B

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

023.60.00.C

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

023.70.00.A

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

Chapter Jan 12/02

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

FI Page

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L 410 WP-E20 MJLINTENANCE SCHEDULE Reference No.

Name of Part/Unit Scheduled Maintenance Check

Frequency

Note

Intentionally left blank.

Chapter Page 4-10

F] Aug 31/95

LETECKE ZAVODY a.s. L 410 UVP-E20 M-AINTENANCE - - - ---

Reference No.

- --

SCHEDULE

- - -

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

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)

3t latest after 48 months

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

- V14, V212, (on 26th transition

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)

Chapter Jan 12/02

10241 Page 4-11

LETECKE ZAVODY a.s. L 410 UVP-E20 M2XINTENANCE

Reference No.

SCHEDULE

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

- 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 Page 4-12

10241 Jan 12/02

LET L 410 UVP-E20 PJlAINTENANCE S C H E D U L E -

N a m e of P a r t / U n i t Scheduled Maintenance Check

Reference No.

Frequency Note

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 o v e r t o t h e t e s t room. A f t e r t e s t i n g mount it a g a i n 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 t e s t room f o r :

s e c u r i t y of a t t a c h m e n t of the torsion bar

clean and i n s p e c t t h e s t a t o r and r o t o r .

Inspect t h e alternator. 024.30.01.B

(MM Engine w/p 80.11.00.a)

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

Remove t h e LUN 2132.02-8 s t a r t e r - g e n e r a t o r and hand it o v e r t o t e s t room. A f t e r t e s t i n g mount it a g a i n i n t h e aircraft.

Check t h e brush l e n g t h and t h e commutator on t h e LUN 2132.02-8 s t a r t e r generat o r a t t h e t e s t room. Remove t h e LUN 2167.03-8 v o l t a g e r e g u l a t o r from t h e 3 i r c r a f t and hand it o v e r t o t h e t e s t room. A f t e r t e s t i n g nount it a g a i n on t h e 3ircraf t

Aug 31/98

Page 4-13

LETECKE ZAVODY a.s. L 410 W P - E 2 O M2kINTENANCE SCHEDULE Reference No.

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

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.

After 3 months at the latest.

Recharge and inspect the batteries.

After 3 months at

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.

Chapter Page 4-14

I=[ Jan 12/02

LET L 410 UVP-E20

MAINTENANCE

Reference No.

SCHEDULE

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

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.

Do after finishing the inspection.

Inspect the socket of the SRAP 500 external power source. Check the operation of the switch with the V 016 electromagnetic tripping.

Chapter Aug 31/98

/024/ Page 4-15

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MAINTENANCE Reference No.

SCHEDULE

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

Intentionally left blank.

Chapter 10241

Page 4-16

Aug 3 1 / 9 5

LETECKE ZAVODY ass. L 410 UVP-E20 -1NTENANCE SCHEDULE Reference No.

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

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.

Only on aircraft where the partion is installed.

Inspect the structure of the nose and rear luggage compartment.

Chapter Jan 12/02

10251 Page 4-17

LET L 410 UVP-E20 MAINTENANCE SCHEDULE Reference No.

Name of Part/Unit Scheduled Maintenance Check

Inspect the fastening belts. Inspect the cargo-related equipment. Examine the emergency equipment (first-aid box).

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.

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.

Chapter Page 4-18

Only in case mounted in the aircraft.

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

F 1 Aug 31/98

LET L 410 UVP-E20 MAINTENANCE SCHEDULE -

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

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

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

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.

Chapter

Aug 31/95

FI Page 4-19

LETECKE ZAVODY a.s. L 410 UVP-E20 IXLAINTENANCE

SCHEDULE -

Reference No.

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

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

After 12 months at least.

Blow through the extinguisher piping with pressure air.

After 12 months at least.

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.

After 12 months at least.

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

Chapter Page 4-20

3nly in case if mounted on the aircraft.

bl Jan 12/02

LETECKE ZAVODY a . s . L 410 UVP-E2O

MAINTENANCE Reference No.

SCHEDULE

Name of P a r t / U n i t Scheduled M a i n t e n a n c e Check

Frequency Note

?LIGHT CONTROLS Cnspect t h e b y - p a s s e s 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 zentres . Inspect 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 o f 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 .

rhe a d j u s t nent of t h e ; e n s i o n of :ables :ontrolling the rudder md t r i m t a b s of t h e = l e v a t o r is lone with the seasonal naintenance - see ?art 6.

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 .

4fter 24

2+.

...d o

w i t h e v e r y second check 2

Chapter J a n 12/02

nonths a t least.

10271 Page 4 - 2 1

LETECKE ZAVODY a . s . L 410 W P - E 2 0 MAINTENANCE SCHEDULE Reference No.

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

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.

After 24 months st least.

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 Page 4-22

10271 Jan 12/02

C 4J

F; Id

a k

C 0

-d c,

(3s

a)+' rl -d

Id a)

W Id

Q) C 4 c, A U Id w c, E

c, 4 . 4

O k X kc, U 4J O C Q ) O C U Uc,

LET L 410 UVP-E20

MAINTENANCE Reference No.

SCHEDULE

Name of Part/Unit Scheduled Maintenance Check

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 Page 4-24

(0271

Frequency Note

LET L 410 UVP-E20 PJIAINTENANCE SCHEDULE N a m e of P a r t / U n i t Scheduled Maintenance Check

Frequency Note

FUEL

I n s p e c t whether t h e r e i s no i n d i c a t i o n of f u e l l e a k a g e on t h e lower wing s u r f a c e i n the engine space before t h e Eire w a l l s . "eck whether t h e r e is no f u e l l e a k a g e from t h e d r a i n t u b e s and d r a i n h o l e s of f u e l tanks.

Carry o u t with airplanes having rubber f u e l tanks o l d e r than 5 years.

Zheck t h e passage of t h e f u e l piping. I n s p e c t t h e p i p i n g and h o s e s ~f t h e f u e l system.

After 4 8 months a t least. Hoses operated for more t h a n 5 years must be visually inspected after e w y 300 f l i g h t hours.

Inspect 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 screens i n the f i l l i n g branches of f u e l t a n k s .

Chapter A u g 31/95

After 1 2 months a t least.

/0281 Page 4 - 2 5

LET L 410 UVP-E20

MAINTENANCE Reference No.

SCHEDULE

Name of Part/Unit Scheduled Maintenance Check

Check wing tip tanks condition.

Frequency Note

Only in case if mounted on the aircraft.

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.

... do with

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

every second

check 2.

Chapter Page 4-26

/0281 May 15/98

LET L 4 1 0 WP-E2O MAINTENANCE SCHEDULE

Reference No.

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

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 .

3nly with 2ircraft uith end tanks.

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.

Chapter May 15/98

/ozsl Page 4-27

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MAINTENANCE Reference No.

SCHEDULE

Name of Part/Unit Scheduled Maintenance Check -

Frequency Note

- --

Intentionally left blank.

Chapter Page 4 - 2 8

/0281 May 15/98 R

LET L 410 UVP-E20 MAINTENANCE S C H E D U L E

Reference No.

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

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 engine nacelle

of the

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

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

Page 4-29

LETECXE ZAVODY a . s .

L 410 UVP-E20 MAINTENANCE SCHEDULE Reference No.

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

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.

see 029.00.00.D

Deslime the main and emergency hydraulic tanks.

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

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

Page 4-30

10281 Jan 12/02

LET L 410 UVP-E20 MAINTENANCE S C H E D U L E Name of Part/Unit Scheduled Maintenance Check

Frequency Note

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 May 15/98

10291 Page 4-31

LETECKE ZAVODY a.s. L 410 UVP-E20 P.2AINTENANCE

Reference No.

SCHEDULE

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

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. Chapter 1

Page 4-32

FI Jan 12/02

LET L 410 W P - E 2 0 PJlAINTENANCE SCHEDULE

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

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.

After 6 months at least.

Check the condition of the compensator in the air distribution. Inspect the condensate pit of the de-icing system of the airframe.

3nly in

case when it is mounted on the aircraft.

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.

Aug 31/95

Page 4 - 3 3

LET L 410 UVP-E2O L v l A I N T E N A N C E SCHEDULE

Reference No.

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

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 surfaces. 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

After 12 months at least.

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

Page 4-34

Aug 31/95

LET L 410 W P - E 2 0 MiAINTENANCE SCHEDULE Reference No.

Name of Part/Unit Scheduled Maintenance Check

Inspect the protecting coat of wiper levers.

Check the wipers.-

Frequency Note

After 6 months 3t least.

operation of -

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.

Chapter May 15/98

/030/ Page 4-35

LET L 410 UVP-E20

MAINTENANCE Reference No.

Name of Part/Unit Scheduled ~ a i n t e n a n c eCheck

Chapter Page 4 - 3 6

SCHEDULE

1030

Frequency Note

1 May

15/98

LET L 410 UVP-E20 MAINTENANCE S C H E D U L E

Name of Part/Unit Scheduled Maintenance Check

Reference No.

Frequency Note

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 o n t h e 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.

Chapter Aug 31/95

Only in case mounted in the aircraft.

1 031 1 Page

4-37

LET L 410 UVP-E20 MJ%INTENANCE

Reference No.

SCHEDULE

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

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.

Only in case when mounted in the aircraft.

Calibrate and record all analogous parameters and single commands and their decoding of the board recorder.

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

Check the dampers of the ZBN 1-1 recorder.

case when mounted in the aircraft. Check the driving belt of the feed mechanism of the MLP-23 tape of the ZBN 1-1 recorder.

Chapter Page 4-38

F] Aug 31/98

....

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

Reference No.

Name of Part/Unit Scheduled Maintenance Check

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 3ircraft. 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 Jan 12/02

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 .

10311 Page 4-39

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Name of Part/Unit Scheduled Maintenance Check

Frequency Note

Intentionally left blank.

Page 4-40

Aug 31/95

LET L 410 WP-E20 MAINTENANCE S C H E D U L E Reference No.

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

LANDING GEAR Yfter 300 landings at least.

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.

landings at least.

............................. 2+...

do with every second check 2. Chapter

Aug 31/95

10321 Page 4-41

LET L 410 W P - E 2 0

SCHEDULE

MAINTENANCE Reference No.

Name of Part/Unit Scheduled Maintenance Check

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

Frequency

4 t

Note

After 600 landings at least.

Examine the blindings (of 1inen a n d metil ) of the main landing gear leg. Check the pressure and the springing values of dampers of the main landing gear leg.

After 300 landings at least.

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.

After 1800 landings 3-t least .

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

After 300 landings 3t least.

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

Page 4-42

032/ May 15/98

LET L 410 UVP-E20 MAINTENANCE SCHEDULE

Reference No.

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

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-passeswithin 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.

After 300 landings at least.

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.

May 15/98

Page 4-43

LET L 410 WP-E2O MAINTENANCE S C H E D U L E Reference No.

Name of Part/Unit Scheduled Maintenance Check

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)

Frequency

After 1800

at least.

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

After 300 landings at least.

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 .

After 1800

landings at least.

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.

Page

4-44

Jul 15/99

LET L 410 UVP-E20 IXAINTENANCE S C H E D U L E

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

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.

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

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

May 15/98

After 24 months or 1 800 landings at least.

Page 4-45

LETECKE ZAVODY a.s. L 410 UVP-E20 MAINTENANCE

SCHEDULE

Name of Part/Unit Scheduled Maintenance Check

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

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 . -

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

After 24 months or 1800

Inspect landing - wheel 3eplace

the wheel of the nose gear: disks completeness the packing rings.

landings at least.

Chapter 1

Page 4-46

Jan 12/02

LET L 410 UVP-E20 M A I N T E N A N C E SCHEDULE

Reference No.

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

After 6 months at least.

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 .

After 12 months at least.

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.

Chapter May 15/98

After 1 800 landings at least.

After 300 landings at least.

/a32/ Page 4-47

LET L 410 UVP-E20

MAINTENANCE Reference No.

SCHEDULE

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

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.

After 2 400 landings at least.

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.

After 900 landings at least.

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.

Chapter Page 4-48

Fl May 15/98 R

LET L 410 UVP-E20 MAINTENANCE SCHEDULE

Reference No.

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

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.

Chapter Aug 31/95

Only in case when mounted or the aircraft.

10331 Page 4-49

LET L 410 UVP-E20 M A I N T E N A N C E SCHEDULE Reference No.

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

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

Examine fixing of storage batteries. Measure the voltage.

Chapter Page 4-50

/ / 03 3

Aug 31/95

LETECKE ZAVODY a.s. L 410 UVP-E20 MAINTENANCE SCHEDULE

Reference No.

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

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

After 24 months at least.

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

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

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.

Chapter Jan 12/02

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

10341 Page 4-51

LET L 410 UVP-E20 M A I N T E N A N C E SCHEDULE Reference No.

Name of Part/Unit Scheduled Maintenance Check

Frequency

Check the permisseble inaccuracies on the LUN 1113.x~-8air-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 recorier

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

Chapter Page 4-52

10341 May 15/98

LETECKE ZAVODY a.s. L 410 UVP-E20 M A I N T E N A N C E SCHEDULE --

Reference No.

Name of Part/Unit Scheduled Maintenance Check

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.

Frequency Note

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

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.

Chapter Jan 12/02

Only when mounted in the . aircraft.

10341 Page 4-53

LET L 410 WP-E20 I?rZAINTENANCE

SCHEDULE -

Reference No.

- -

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

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.

034.22.02.C Check on the AGR-74-5 /MM-AGR-74 artificial horizon at the test room the following: techno1 . - starting time process 034.22.00. - necessary current - operation of the push button *a)/ - operation of the stabilizer of the failure of the artificial horizon - transmitter signal - difference of voltage divider signal and transmitter - rate of bank and longitudial incline - inaccuracy of data on the tilting table. Inspect the artificial horizon.

Chapter I

Page 4-54

Only in case when mounted in the aircraft.

FI Aug 31/95

LET L 410 UVP-E2O MAINTENANCE S C H E D U L E Reference No.

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

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.

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

Chapter Aug 31/95

1 1 034

Page 4-55

LETECK~ZAVODY a.s. L 410 WP-E20 J?XAINTENANCE

Reference No.

SCHEDULE

Name of Part/Unit Scheduled Maintenance Check

Frequency

Note

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. Only in case when mounted in the aircraft.

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.

After 24 months least.

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 Page 4-56

L Jan 12/02

LET L 4 1 0 WP-E2O IYLAINTENANCE S C H E D U L E

Reference No.

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

3nly in case when installed in the aircraft.

OXYGEN

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

Inspect the oxygen masks and check its operation.

Chapter Aug 31/95

/ 1 035

Page 4-57

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Name of Part/Unit Scheduled Maintenance Check

Frequency Note

Intentionally left blank.

Page 4-58

Aug 31/95

LET L 410 W P - E 2 0 MAINTENANCE SCHEDULE -

Reference No.

ppppp

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

WATER WASTE

Chapter Aug 31/95

j0381 Page

4-59

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L 410 UVP-E20 MAINTENANCE SCHEDULE Name of Part/Unit Scheduled Maintenance Check

Reference No.

Frequency Note

Intentionally left blank.

Page 4-60

A u g 31/95

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SCHEDULE

MAINTENANCE

Reference No.

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

STANDART PRACTISES AND STRUCTURES-GENERAL Inspect the skin aircraft . Inspect the paint aircraft.

of the

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

After 24 months 2t least. After 24 months 3t leas$.

Check the tightening of screws of removable covers being a part of the bearing skin. Inspect the draining openings of the airframe.

Chapter Aug 31/95

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Reference No.

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

'heck the main and emergency loor and their suspensions. 'heck the reliability of locks. Grease the lock of the loor. X e c k 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.

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Frequency Note

LET L 410 UVP-E20 MAINTENANCE SCHEDULE

Reference No.

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

FUSELAGE

Examine the rubber parts of the fuselage.

ifter 24 nonths it least.

Check the state of components made of laminated glass.

ifter 24 nonths it least.

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

Aug 31/95

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M2iINTENANCE

Reference No.

SCHEDULE

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

Check the floor in the pilot's cockpit.

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

kf ter 6aonths 3t least.

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-fuselagel', "tail areas - fuselage". Inspect the transition guards of the fuselage with the wing and tail areas.

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Reference No.

054

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

NACELLES

054.00.00.A Inspect the air channels. 054.00.00.C Inspect the engine nacelles (frame and skin). 054.00.00.D Check the packing flags, rubber parts and leather packing elements in the dividing planes of guards. 054.00.00.E Check the setting of lever locks of engine guards.

2+...

do with every second check 2.

Chapter Aug 31/95

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Reference NO.

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Frequency Note

STABILIZERS Inspect the tail surface. Inspect the elevator and rudder. Inspect the edge bands on the tail surface.

4f ter 3 months 3t least.

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.

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WINDOWS Inspect the windscreen.

After 6 months

3t least. Inspect the windows of the passenger cabin.

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Frequency Note

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

After 12 months at least.

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.

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Reference No.

Name of ~art/Unit Scheduled Maintenance Check

Frequency Note

Zheck the radial and axial zlearance of bearings of moring areas and their proper securing. Zheck the surface of leading sdges of wing flaps and slots in places where a contact may x c u r between the wing flap ~ i t hthe 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+...

Page 4-74

9fter 24 nonths 3 t least.

do with every second check 2.

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Reference NO.

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

PROPELLER Inspect the propeller the propeller speed limiter, the electrohydraulic controller, auxiliary pump, pressure switch and collector. 061.00.10.C Inspect the trasmission (Prop. MM) system of the feedback. Check the system of the compound coupling. 061.00.10.D Inspect the clearance between (Prop. MM) the slide blocks and thrust ring.

30 also

3fter the first 10 30UrS.

061.10.00.D Check the fixing of the front (Prop. MM) propeller cover. 061.10.00.F Check the securing of the (Prop. MM) propeller. 061.10.00.H Inspect the conductors. (Prop. MM)

Do also 3fter the first 10 hours.

061.10.00.1 Inspect the joints on the (Prop. MM) propeller.

Do also 3fter the first 10 hours.

061.10.00.J Inspect the propeller cover. (Prop. MM) 061.20.01.A Clean the LUN 7816 propeller (Prop. MM) speed governor.

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Frequency Note 1

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.

Chapter Page 4-76

- - - +

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-1NTENANCE Reference No.

SCHEDULE

Name of Part/Unit Scheduled Maintenance Check

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

061.00.10.E - operation of the propeller (Prop. MM) speed limiter 77.15.00.a (Engine MM page 505)

operation of the torque channel

77.55.00.a (Engine MM)

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

77.56.00.a - operation of the LUN 5223 (Engine MM) generator speed derivative element 2+... do with every second check 2. Chapter Aug 31/98

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-1NTENANCE Reference No.

371.20.00.A

Name of Part/Unit Scheduled Maintenance Check

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

Chapter Page 4-78

SCHEDULE Frequency Note

lo also sith every zhange of che engine.

/071/ Aug 3 1 / 9 5

LET L 410 UVP-E20 MAINTENANCE SCHEDULE

Reference No.

Name of ~art/Unit Scheduled Maintenance Check

Frequency Note

601 E OR M 601 E-21 ENGINE

072.02.00.A Check visually the fixing of (Engine MM instruments of the fuel and oil installationstfixing of W/P 72.02.00.a) the startergenerator,alternator and ignition. 072.02.00.B Inspect the electric system (Engine MM of engine instruments. W/P 72.02.00.b) 072.22.00.A Inspect the air bulkhead. (Engine MM W/P

72.22.00.a) 072.23.00.A Inspect the inlet screens (Engine MM of the engine.

072.33.00.A Inspect the engine (Engine MM suspensions.

W/P

72.33.00.a)

072.90.00.A Inspect the magnetic plugs of (Engine MM the reducer,drive boxes and oil tank. W/P 79.10.00.c)

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

072.90.00.B Replace the insert of the (Engine MM oil cleaner.

W/P

79.10.00.b) 2+....do with every second check 2. Chapter

)0721 Page 4-79

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SCHEDULE Frequency Note

qith every l f t e r 300, 300 a n d L500 h o u r s . 4fter 12 nonths a t

( E n g i n e MM

W/P

79.50.00.a 79.50.00.c)

Least.

Chapter Page 4-80

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MAINTENANCE Reference No.

SCHEDULE

N a m e of P a r t / U n i t S c h e d u l e d Maintenance Check

Frequency Note

E N G I N E FUEL AND CONTROL 073.11.00.A ( E n g i n e MM W/P

73.11.00.a)

073.22.00.A ( E n g i n e MM

I n s p e c t t h e components and piping of engine f u e l system under t h e e n g i n e c o w l i n g s and the i n l e t chanel.

I n s p e c 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+...

Aug 3 1 / 9 5

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

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Frequency Note

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Frequency Note

IGNITION 374.10.00.A (Engine MM

;J/P

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

30.21.00. page 501)

374.10.00.B (Engine MM

Replace the low-voltage spark plugs.

;J/P 30.22.00 page 401)

2+...

do with every second check 2.

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Frequency Note

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Reference No.

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

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 kinematics motion of the engine controls.

Carry out also with any exchange of the engine.

.............................. 2+...do with the first check : and then with every second check 2.

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J u l 15/99

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076.10.00.A Check the clearance V 3 . (Engine MM W/P 76.10.00.b) 076.10.00.B Check the motion of the (Engine MM- "Bc If 1 ever. -

W/P

76.10.00.c) 076.10.00.C Check and adjust the length of (Engine MM the push-pull rod.

W/P

76.10.00.e)

076.10.00.D Check the operation of the (Engine MM engine controls. Lubricate the spherical bearings and the W/P 76.10.00.g) feathering pick-up lever.

E Wash dnd lubricate the automa076.10 .-00-. (Engine MM tic feathering switch lever. W/P 76.10.00.h) 076.10.00.F (Engine MM W/P 76.10.00.a)

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

076.10.00.G Check the end positions of the (Engine MM control lever of the fuel closing cock. W/P 76.10.00.d) -

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

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O76.lO.00 .E Check the operation of the (Engine MM limiter system under the operation of engines. W/P 77.55.00.b)

Frequency Note

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

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.

Chapter May 15/98

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Reference No.

Name of Part/Unit Scheduled Maintenance Check

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

Frequency Note

076.15.00.B Check on the LUN 1476-8 (Engine MM torque limiter pressure switch at the test room: W/P 76.30.00.a) - basic data - insulation resistance. Inspect the torque limiter pressure switch. Check the adjustment of the LUN 7370-8 fuel valve control. 076.52.00.A (Engine MM W/P 77.52.00.a)

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.

076.52.00.B Check on the LUN 3280-8 (Engine MM automatic feathering pressure switch at the test room: W/P 76.30.00.a) - basic inaccuracies - insulation resistance. Inspect the switch.

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Frequency Note

ENGINE INDICATING Remove the LUN 1347.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 .

? h a 1 fijures zoncern only the zxecution 2f the ;cale.

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.

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Reference No. -

-- - --

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

077.11.00.B Check on the LUN 1540.02-8 (Engine MM torque transmitter set and on the LUN 1539.04-8 torque indiW/P 77.11.00.a) cator 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. 077.22.02.A Remove the LUN 1358-8 oil (Engine MM temperature transmitter from the aircraft and hand it over W/P 77.22.00.b) to the test room. After testing mount it again in the aircraft

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

Page 4-90

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

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No.

Name of Part/Unit Scheduled Maintenance Check

Frequency Note

EXHAUST 078.10.00.A (Engine MM

Inspect the

exhaust bends.

W/P

78.10.00.a)

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Frequency Note

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Frequency Note

079.30.00.A Zheck the oil amount in the tank by means of a gauge. (Engine MM ~ i l W/P 79.50.00.b) 079.40.00.A Carry out visual inspection ~f oil system hoses.

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

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.

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Frequency Note

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Frequency Note

STARTING

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

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Frequency

Chapter 10801

Page 4 - 9 6

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Name of Part/Unit Scheduled Maintenance Check

Frequency Note

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

Jan 12/02

Do in case the pump was depreservec

....carry

out with every 4th check 1

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5 INSPECTION

Aug 31/95

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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 airplane takeover by customer or from dateof t h e latest overhaul or from the previous inspection.

'------I--

- -

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 I I I I I

1 -

5.1.4. Based on the results of the inspection, the necessary repairs must be carried out so that the required flight safety level i s secured a s well-as the ability of the aircraft to fly till the next inspection. -

I I I

- -

I I

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

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6 S E A S O N A L

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LET L 410 UVP-E20 MAINTENANCE SCHEDULE 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. -

6.2. Works which must be carried out with temperature decrease

Name of Part/Unit Scheduled Maintenance Check

Reference No.

Note

FLIGHT CONTROLS Adjust the tension of the control cables in the rudder and elevator trim tabs. HYDRAULIC BOWER 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

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MAINTENANCE Reference No.

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Name of Part/Unit Scheduled Maintenance Check

Note

NAVIGATION Check the errors of the Rn 4 5 ambient air thermometer. PROPELLERS Check the cycle time of the LUN 2 6 0 1 - 8 propeller time relay.

16.3. Work which must be carried out with temperature increase

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.

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LET L 410 UVP-E20 MAINTENANCE SCHEDULE

6.4. Limitations of the operation (maintenace)

The limitation for the operation is given in the L410 W P - E 2 0 Maintenance Manual, section 012.

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UNSCHEDULED

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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 permisible - maximum landing weight.

higher

than

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 .

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LETECKE ZAVODY a.s. L 4 1 0 WP-E2O MAINTENANCE S C H E D U L E

7.2. Work done at the unscheduled inspections

Para of the MS or section of the MM

NOTE:

Hard landing

Lighting strike, Landing at weight flight in the higher than max. storm activity landing weight

@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 LG certificates (if into the nose and main supplied). -

Page 7-4

Jan 1 2 / 0 2

LET L 410 UVP-E20 MAINTENANCE SCHEDULE

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;

054.00.00.A,C;055.00.OO.A;

053.00.00.B;

056.10.00.B;057.30.0O.A;

061.00.10.A

(Prop. MM

072.22.00.A

(Engine MM ) ; 072.23.00.A

);

053.50.00.A;

061.10.00.J

(Prop.

MM ) ;

(Engine MM ) ;

079.40.01.A.

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STOFL%GE OF

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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 covers.

must be stored provided

with all blinds and

Work done durinq the preparation for storinq 8.2.1.

Work carried out for storing the of 15 to 30 days.

aircraft for a duration

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 W P - E 2 0 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 (this does not concern the tip tanks).

the full

amount

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 MAINTENANCE S C H E D U L E

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 of up to 3 months -

8.2.2.1. Carry out 8.2.2.2

for a duration

work according to items 8.2.1.1. to 8.2.1.10.

Preserve the 061.00.00.)

propeller

see

propeller

MM,

section

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 of more than 3 months

for a duration

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

8.2.3.2.

8.2.3.3. Wash out the main wheel and nose wheel bearings and L CSN 657131 or preserve them with the 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

MAINTENANCE

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 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.

I I

tyres and LIG shock

If the aircraft is stored under tropical and subtropical conditions, clean the windshield with antiseptic means in order to prevent the formation of mildew (ethylalcohol).

8.4. Work done

I I

the pressure in the

Maintenance of the aircraft after any 30 davs of storinq

8.3.2.1.

SCHEDULE

when puttinq

the aircraft

into operation after

storinq 8.4.1. Work done after storinq the

I I

aircraft for a duration of 15

to 30 days

8.4.1.1. Remove the covers from the aircraft.

8.4.1.2.

I I I I I

Remove the preserving wax from the preserved outer surfaces and the landing gear by means of cleaning petrol. Take care greased.

Page 8-6

that the

friction surfaces

are not

Aug 3 1 / 9 5

LETECKE ZAVODY a.s. L 410 UVP-E20 MAINTENANCE S C H E D U L E

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 system. 8,4.1.5. -

preservation

the

water

injection

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 3 months. I

from

aircraft for a duration up to

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 section 72.03.00).

from engines

(see engine MM,

a n d clean- the propeLler 8-4r2.3 .-Remove the-preser~a~ion propeller MM, section 061.10.00). 8.4.2.4. Bleed the suction piping of the hydrulic according to the aircraft MM, section 029.00.00. 8.4.2.5. Refill nitrogen in the hydraulic aircraft MM, section 029.00.00).

(

see

system

accumulators

(see

I I

8.4.2.6. Check the cabin fire extinguisher. 8.4.2.7,

Jan 12/02

Carry o u t the engine t e s t lsee aircraft 071.00.00). -

MM,

section

Page

8-7

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

EISLINTENANCE

8.4.3.

Work done after storinq the aircraft for a duration over 3 months Carry

8.4.3.1.

operations

according

to items

8.4.2.1.

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. -

out

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 4 1 0 UVP-E20 aeroplane ' I .

Page

8-8

Jan 12/02

LET L 410 UVP-E20 MAINTENANCE SCHEDULE

S U P P L E M E N T S

Aug 31/95

Page

9-1

LET L 410 WP-E20

MAINTENANCE

SCHEDULE

Intentionally left blank.

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 o f the-periodicmaintenance - 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 nipples5xx cables, bowden cable hinges, bolts, sliding parts 6xx 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

LET L 410 UVP-E20 MAINTENANCE SCHEDULE

Number 3f lubrid. places.

Name - -

Pcs

gumber of figure

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

Page 9.1-2

Aug 31/95

LETECKE ZAVODY a.s. L 410 UVP-E2O

MAINTENANCE

Number ~f lubrid places.

SCHEDULE

Name

Pcs

!?umber of figure

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

it is carried out during airplane inspection

on the lever of the trim tab control (elevator)

Jan 12/02

it is carried out during airplane inspection

Page 9.1-3

LETECKE ZAVODY a.s. L 410 UVP-E20 MAINTENANCE S C H E D U L E Number >f lubrid. places.

Name

Pcs

Number of figure

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

it is carried out during airplane inspection

countershaft of the nose wheel control

Page 9.1-4

Jan 12/02

LETECKE ZAVODY a.s. L 410 UVP-E20 M A I N T E N A N C E SCHEDULE

Number >f lubrid. places.

Name

Pcs

Jumber of figure

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

it is carried out during airplane inspection

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)

Jan 12/02

Page 9.1-5

LET L 410 UVP-E20 MAINTENANCE

SCHEDULE -

Number of lubrid places.

Name

Pcs

Number of figure

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

Page 9.1-6

Aug 31/95

LETECKE ZAVODY a.s. L 410 UVP-E20 IXAINTENANCE

Number ~f lubrid. places.

SCHEDULE

Pcs

Name

!?umber of figure

?iano hinge of the ground spoiler sliding parts of control levers in the ?ilotlscockpit. 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 ~etweenthe 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

Jan 12/02

it is carried out during airplane inspection

Page 9.1-7

LETECKE ZAVODY a.s. L 410 UVP-E20 MAINTENANCE

Number 3f lubrid. places.

SCHEDULE

Name

levers

Pcs

Number of figure

the heating control

it is carried out during airpla.ne inspection 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 ABC tab

attachment

main landing gear shock absorber lower attachment joint connection of the front baggage compartment door with the fuselage connection of-the n o s e tilting c o n e with the fuselage -

) Page

9.1-8

Jan 12/02

LETECKE ZAVODY a.s. L 410 UVP-E20 MAINTENANCE S C H E D U L E

9.1.3. Lubrication tables arranqed accordinq to the types of

periodic maintenance ( 2 , 3 , 4 )

Scheduled work

Type of periodic maintenance (lubrication place)

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.

Jan 12/02

Page

9.1-9

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

Scheduled work

SCHEDULE

Type of periodic maintenance (lubrication place)

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.

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

LETECKE ZAVODY a.s. L 410 UVP-E20 MAINTENANCE SCHEDULE

Scheduled work

Type of periodic maintenance (lubrication place)

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.

Jan 12/02

Page

LETECKE ZAVODY a.s. L 410 UVP-E20 MAINTENANCE S C H E D U L E

Type of periodic maintenance (lubrication place)

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 - 2 5 O ~the NK-50 grease and at tem eratures below -25gC 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.

Page 9.1-12

Jan 12/02

LET L 410 UVP-E20 M A I N T E N A N C E SCHEDULE 9.1.4. Tables of lubrication points,

the lubrication of which is done in another interval than 300 hours lubrication done once a month

----

Lubrication point

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. 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

Scheduled work 1. Clean with cleaning petrol and

Lubrication point 705

preserve with vaseline (e.g. the L or K-17 preservative vaseline) 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

May 15/98

Page 9.1-13

LET L 410 UVP-E20 MAINTENANCE SCHEDULE

Fig.

9.1

1 TAIL UNIT

detail of the rudder trim tab control assembly detail of the elevator outer hinge bearing with the dust cap

Page 9.1-14

Aug 31/95

LET L 410 UVP-E20 MAINTENANCE S C H E D U L E

Fig.

9.1

NOSE WHEEL STEERING

Aug 31/95

Page 9.1-17

LET L 410 W P - E 2 0

MAINTENANCE

Fig. 9.1

SCHEDULE

5 MAIN LANDING GEAR

Page 9.1-18

Aug 31/95

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

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

Jan 12/02

Page 9.1-15

LETECKE ZAVODY a.s. L 410 UVP-E2O M A I N T E N A N C E SCHEDULE

Fig. 9.1

Page 9.1-16

'WING

Jan 12/02

LET L 410 UVP-E2O MAINTENANCE S C H E D U L E

9.1

6 NOSE

LANDING GEAR

Page 9.1-19

LET L 410 UVP-E20

MAINTENANCE

FIG.

9.1

SCHEDULE

ENGINE CONTROLS AND ENGINE COWLINGS

Page 9 . 1 - 2 0

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 MAINTENANCE S C H E D U L E

9.1

I I

9 FUSELAGE FRONT SECTION

- detail of mechanical windshield wiper

Page 9 . 1 - 2 2

Aug 3 1 / 9 5

LET L 410 UVP-E20 MAINTENANCE S C H E D U L E

Fig. 9.1

10 DOOR AND FRONT AIRCRAFT TILTING CONE

Page 9 . 1 - 2 3

LET L 410 UVP-E20

MAINTENANCE

SCHEDULE

Intentionally left blank.

I I

Page 9.1-24

Aug 31/95

LETECKE ZAVODY a.s. L 410 UVP-E20 MSLINTENANCE

SCHEDULE

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 wing, stabilizer, tail unit Carry out the service - after the performed - if the aircraft has - after the execution 9.2.4.1 - after the performed

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 defined in the Flight Manual the L 410 UVP-E20 aircraft.

Jan 12/02

Page

is of

9.2-1

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

MAINTENANCE

9.2.2.2.

Drain off all fuel.

9.2.2.3.

Fill up the undischargeable fuel amount 6 litres (left side - main fuel tanks 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 levelling points on the fuselage No. maximum difference of 1 mm. -

plane by means of 1 and No. 7 with a ~

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.

9.2.2.10. -

Page

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.

9.2-2

Jan

12/02

LETECKE ZAVODY a.s. L 410 UVP-E20 MAINTENANCE SCHEDULE

9.2.3.

Levellinq of aircraft

9.2.3.1.

Check whether 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

the

aircraft

empty

the

basic

Page 9.2-3

LETECKE ZAVODY a.s. L 410 UVP-E20 SCHEDULE

I?/LAINTENANCE

O~erationcheck

9.2.4. 9.2.4.1.

List of products after replacement of which carry the service test flight.

out

Name of product Works after the execution of which No. of subgroup PTP and marking it is necessary to carry out the service test flight

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

Replacement of one p r both -engines -

Fuel regulator Replacement of the regulator of one or both engines Replacement of one or both propellers

Propeller

Propeller Speed Replacement of one or both regulator propeller regulators

1 Wing

1 Stabilizer

l1 Rudder Ailerons Wing flaps

l~e~lacement of wing (Replacement of stabilizer

Replacement of the -fin -

Replacement of elevator

l~e~lacement 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.

Page

9.2-4

Jan

12/02

LETECKE ZAVODY a.s. L 410 UVP-E20 M A I N T E N A N C E SCHEDULE

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

LETECKE ZAVODY a.s. L 410 W P - E 2 0 MAINTENANCE S C H E D U L E

Intentionally left blank.

1 Page

9.2-6

Jan 12/02

LET L 410 UVP-E20 MAINTENANCE S C H E D U L E

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 M A I N T E N A N C E SCHEDULE Example of Levelling and Rigging Record (page 2)

1. A e r o p l a n e l e v e l l i n q

L a t e r a l datum i s d e t e r m i n e d by l e v e l l i n g p o i n t s go.

1.1.

a n d 1 9 RH / s e e F i g .

L o g i t u d i n a l datum i s g i v e n by t h e f u s e l z g e d a t u m I1

1.2.

d e t e r m i n e d 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 t a b 1 2 on Page 8 . I

I1 I11

Notes:

L e v e l l i n g p l a n e / p a s s i n g t h r o u g h 1 . e v e l l i n g 2 o i n t s Xo . 3 , . 5 , 6 / 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 a n e / Engine r i g g i n g f a c e t

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 the levelling plane.

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 dx i t h , t h e

"-".

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 the right

"+" / t h e LH and

?H ,

"-",

sides are identical

see Fig. 2 .

Fig.

Page 9 . 2 - 8

sign

A u g 31/95

LET L 410 UVP-E2O M-AINTENANCE SCHEDULE Example of Levelling and ~ i g g i n gRecord (page 3 )

2 . C h e c k 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 plane

see F i q .

CAUTION: FOLLOVTING TABLE LDPLIZS FOR Z R O P L X T S a3C.M. 1 6 t h S E R I Z S -

WITH WING T I ? FUEL TAX'XS FROM

~1 ignment

I !

Nominal

Yeasurenent SO. 1

~ ~ R I A~ L5- 8.b 1 6 0 1 , ?!easuze~en~ go.

Xeasuremenc No. 3

Check o f winq 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 to t h e levellinq plane CAPTION:

- see

Fig.

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 S E R I A L No. 8 6 1 6 0 1 .

Rear Front D i f f e - Tolel e v e l l i n g Levelling rence rance po i n c point

Aug 31/95

Uezsurement So. 2

Xeasurernent Yo. 1

64.78

210

LH!

64.78

210

Xeasurement No. ?

Page

9.2-9

LET L 410 UVP-E20 M2lINTENANCE SCHEDULE Example of ~ e v e l l i n gand ~ i g g i n gRecord (page 4)

Check o f wing t i p 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 t h e

aeroplane axis

see Fig. 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.

r A 1 ignment

Nominal value

Tolerance

5 . Check o f Aliqnment D Check o f Alignment E

see Fig.

Yeasurement !'a. 1

851601.

Yeasurement Xo. 3

Yeasurenent Yo. 2

/measured i n t h e ~ r o u e l l e rs h a f t a x i s / /measured from p l a n e I1 t o I I I /

Nominal

Xeasurement

Yeasurement

NO. 2

.Neasurement No.3

The d i f f e r e n c e between D and E m u s t n o t e x c e e d 3 nun. T h e . a l i g n m e n 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

LET L 410 UVP-E20 -1NTENANCE SCHEDULE -

Example of ~ e v e l l i n gand Rigging Record (page 5 )

6. Check of f u s e l a g e s a g and ~ w i s t- see F i q .

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

h l ignmen t

A u g 31/95

Nominal

Ileasur-.=enc

s e e ?ig. 1

>!easur+3enc !lo.

!-!easurenec 90. 3

Page 9.2-11

LET L 410 UVP-E20 MAINTENANCE SCHEDULE

Example of Levelling and Rigging Record (page 6 )

1 9 9 7 9 . 5 / t h e o r e t i c dimension/

for aeroplanes with

wing t i p f u e l t a n k s I!

Page 9.2-12

1 9 4 7 8 . 9 / t h e o r e t i c dimension/

for a e r o p l a n e s with wing t i p s

A u g 31/95

LET L 410 UVP-E20 MAINTENANCE SCHEDULE

Example of Levelling and Rigging Record (page 7 )

8. Check of alignments F, G /measured in the propeller shaf'

see F'icl.

axis

TLerance

:4e.asurcment Yo.

ueasurenent Yo.

~easurezent !lo. 3

The check of engine alignment to be carried out prior the propeller installation. 9.

Check of alignments A, B

see 'ig.

Alignment

Xeasurement Yo, I

Tolerance

Measure3enc No. 2

. Yeasurement Yo.

A ItY

.\ - .$

Xax.difference 15

w BL

Xax.difference

Subcript L = left hand, ? = right hand side.

Page

9.2-13

LET L 410 W P - E 2 0 M.AINTENANCE SCHEDULE -

Example of Levelling and Rigging Record (page 8)

10. C h e c k of fuselage curvature - s e e

11. C h e c k of w i n g twist

Fic.

see Fig. 3

,eve11ing ioninal Tolerance value points

!!easuremsnc Lfeasurernent Xeasurement Yo. 1 Yo. 2 ?To. 3 I

20.25

+ 4 -

1 8241

ii 13.98

-+ 4

LII -1

Page 9.2-14

.oo

+ -

Aug 3 1 / 9 5

LET L 410 UVP-E20 I??LAINTENANCE

SCHEDULE

Example of Levelling and Rigging Record (page 9 )

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

of incidence

s e e Pic. 3

Level 1 in: Yominal po i n t s value

A 1 ignmen t

42.37

23-24 lower

Xeasurezent >!easnrernent 3 e a s u r e n e n t 1 !TO. 3 So. 2

cranc

-3

I 2i

. 28.7

1 I

iH i

13. Check of s t a b i l i z e r ?oslz.:c?.

t o s e c u r e a 2"

A 1 ignnen t

A u g 31/95

z s l z t i v e ?o I ? v e l l i n g e l x e a n g l e oE i n c l j , a n c e - s e e ? i ~ .2

Level1 ing Yoninz, , -a;simcei points val ~e '

Xeasurezecx tl U e a s u r e ~ ~ !-feasurernenc ~t ,.do. i YO. 2 YO. 3

lower

Page 9.2-15

LET L 410 UVP-E20 MAINTENANCE SCHEDULE Example of Levelling and Rigging Record (page 10)

Fig. 3 14. Check of aliqnment C

see Pig. 3

Tolerance

A 1 ignmen t

1 I

VC? %..al x.

Page 9.2-16

difference 15

A u g 31/95

LET L 410 UVP-E20 MAINTENANCE SCHEDULE Example of Levelling and Rigging Record (page 11)

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 CAUTION:

see Tic. 3

FOLLOWING TABLE A P P L I E S FOR AEROPLXUES FRCX 1 6 ~ 5SZ?.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 value

Aug 3 1 / 9 5

Tolzrance ? r ~ a . }Oper. - -

.easurement Ueasurmenc Yo. I Yo. 2

Yo.

Page 9.2-17

LET L 410 UVP-E2O MAINTENANCE SCHEDULE

Example of Levelling and Rigging Record (page 12)

V a l u e s 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 .

Values i d e n t i f i e d with 11

apply f o r levelling points

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 o f wing p o s i t i o n I

A1 ignmen t

Prod.

293'55 287.55*

+ -

- see Fig. A1 ignment

Page 9.2-18

= P r o d u c t i o n ; Oper.

1 7 . Check of l a n d i n g gear

3 Xeasureaent Xeasurement Xeasurement ?lo. 2 YO. 3 Yo. 1

L e v e l l i n g Xorninal T o l e r a n c e value points Prod. Oper. 19-1 1

see F i g .

= Operation

f m s s s u r e d i n &loaded

condition/

YOminal value

Tolera.~ce

Yeasurenent No. 1

Xeasurement Yo. 2

Yeasurement Xo. 3 9

Aug 3 1 / 9 5

UJii

L 410 UVP-E20 mINTENANCE SCHEDULE Example of ~ e v e l l i n gand Rigging Record (page 1 3 )

la.

Check of r u d d e r a n d r u d d e r t r i m tab def1ec:icns

11ignmen t Angle

XorninaL Xeasurezent Tol_era_nce_ value o 1

!!easare~ent

-see Fig.

-YO? 7 -

.Xeasure~enc XO-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 h e u g p e r Itf= end of che ~ r L 3tab. . . X = 25 - 3 . 9 m a 2 a s u r e d on =he - ? p e r r:q-r 2nd of ~ 3 - et r i n t 2 b .

A u g 31/95

Page 9.2-19

LET L 410 UVP-E20 MAINTENANCE SCHEDULE -

Example of ~ e v e l l i n gand Rigging Record (page 14)

1 9 . Check o f 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

Fig.

Wing datum

1 / omi in all

A 1 ignment Angle

value

Toierance/

/ ~ e r s u r e r ; e n tYersurernent Y e a s u r c r e o t 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 MAINTENANCE SCHEDULE

Example of Levelling and Rigging Record (page 15)

20.

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

s e e Fiq. 6

Fiq. 6

I1 = Fuselage datum VI = H o r i z o n t a l s c a b i l i z e z datum

~ol2rmc.j

Xeasur+nent Xeasurement Xeasurernen No. I 0 . 2 Yo. 3

Subscript H = u p , D = EO:VT.

Page 9 . 2 - 2 1

LET L 410 UVP-E20 MAINTENANCE SCHEDULE Example of Levelling and Rigging Record (page 16)

21.

Nosewheel s t e e r i n g a n g l e Y

= m a n u a l mode

= p e d a l mode

Fig.

see fig. 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 i d e .

Page 9.2-22

Aug 31/95

LET L 410 UVP-E2O M A I N T E N A N C E SCHEDULE

Example of Levelling and Rigging Record (page 17)

Check o f o u t e r a n d i n n e r x i n g f l a p d e f l e c t i o n s

22.

Flaps i n take-off

22.1.

position

s e e Pig. 8

Angle

6 1l s p e c i f i e s t n e take-off

position of o u t e r f l a p s

Angle

s p e c i f i e s the t+ke-off

?ositior, of i n n e r f k 3 s

F l a p Yominal Alignment p o s i - v a l u e o f tion the angle 6

2 0

c o u w o

u4.d

w w

4 Mu

18'

-lo

rV .I

8 . u-

C a J I I O

.2J* =.

measured

I .iEi

1 1

Page

9.2-23

LET L 410 UVP-E2O M A I N T E N A N C E SCHEDULE Example of Levelling and Rigging Record (page 18)

22.2.

Flaps i n landing position

s e e Fig.

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 21 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 o f i n - e r f l a p s

x / Nominal v a l u e o f 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 3/

obta,$ned d u r i n g m e a s u r e m e n t s 30. ! / 2 ,

Fig.

-lo0.

9 7

Flap Nominal Alignment posi- value o f Tolerance tion angle

Page 9 . 2 - 2 4

Xeasurement Zeasurenent Xeasureaent No. 1 1 x0.2 No. 3 I

A u g 31/95

LET L 410 UVP-E20 MZkINTENANCE S C H E D U L E

Example of Levelling and Rigging Record (page 19)

Ueasurement Sfeasurement Ueasurement NO. 1 No. 7 Yo. 3

Xl ignmen t

Subscript L = left h a n d , 2 =

------?:A-

side.

Page 9 . 2 - 2 5

LET L 410 UVP-E20

MAINTENANCE

SCHEDULE

Example of Levelling and ~ i g g i n gRecord (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

Fig.

see P i g .

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 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 N 0 . i N o . 2

No.

Date Organization: S i q n a t u r e of t h e responsible person

Page 9 . 2 - 2 6

A u g 31/95

LET L 410 UVP-E2O MAINTENANCE SCHEDULE 9.2.4. Operation check 9.2.4.1. List of products after replacement of which carry the service test flight.

out

Name of product Works after the execution of which No. of it is necessary to carry out the subgroup PTP and marking service test flight M 601 E or M 601 E-21 Engine

Replacement of one or both engines

Fuel regulator Replacement of the regulator of one or both engines Propeller

Replacement of one or both propellers

Propeller Speed Replacement of one or both propeller regulators regulator Wing

Replacement of wing

Stabilizer

Replacement of stabilizer

Fin

Replacement of the fin

Elevator

Replacement of elevator

Rudder

Replacement of rudder

Ailerons

Replacement of one or both ailerons

Wing flaps

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 MAINTENANCE SCHEDULE

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 W P - E 2 0 aeroplane. -

CAUTION: ALL LIMITATIONS GIVEN IN THE FLIGHT MANUAL OF THE L 410 W P - E 2 0 AEROPLANE MUST BE KEPT DURING THE CHECK FLIGHT.

I I

Page

9.2-28

Aug 31/95

LET

L 410 WP-E20 MAINTENANCE SCHEDULE Reason of

check flight

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 o f engine starting Zheck of the IELU Taxiing

Page

9.2-29

LET

L 410 UVP-E20 MAINTENANCE SCHEDULE Reason of the check flight

Name of work

(check)

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 - 3 0

Aug 31/95

LET L 410 UVP-E20 MAINTENANCE S C H E D U L E Reason of the check flight

Name of work

(check)

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 W P - E 2 0

MAINTENANCE

SCHEDULE

Reason of the check flight

Name of work

(check)

Check of operation and efficiency of heating in the cockpit and pasenger compartment -

Check of oiltemperature 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 S C H E D U L E Reason of the check flight

Name of work (check)

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 kof the response of the aeroplane in dependence on elevator control force

Aug 31/95

Page 9 . 2 - 3 3

LET L 410 UVP-E20

MAINTENANCE

SCHEDULE

Reason of the check flight

Name of work (check)

Acceleration of the flight to ax =350 km/hr I A S d e c k of the response of the aeroplane in dependence on elevator control force Cruise 34

Check of engine and propeller performance at Maximum Continuous power Check of ability to trim and control of the aircraft

3 6 POWER control lever

and PROP control lever setting check 37

Flight check

Page 9.2-34

A u g 31/95

LET L 410 WP-E2O PJILAINTENANCE

SCHEDULE

Reason of the check flight

Name of work (check)

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 4 1 0 WP-E20

MAINTENANCE

SCHEDULE

Reason of the check flight

Name of work (check)

Check of operation of ILS, radio altimeter, audio switch box, special equipment Check o f 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 flapsextension -

Page 9.2-36

Aug 31/95

LET L 410 W P - E 2 0 MAINTENANCE SCHEDULE

Reason of the check flight

Name of work (check)

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-off Work close-up Routine maintenance B

Page 9 . 2 - 3 7

LET L 410 WP-E2O

MAINTENANCE

SCHEDULE

Reason of the check flight

Name of work (check)

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 MAINTENANCE SCHEDULE

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 wing tip tanks.

for the

fuel transfer

check from the

Fill-up the fuel in following amounts:

- main fuel tanks

wing tip tanks

400 kg left side 400 kg right side 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

SCHEDULE

MAINTENANCE

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

17.

increase the speed of the gas shifting of POWER control lever read the torque at which signal lamp goes on the value

Check of engine and power setting.

Page 9.2-40

the signalling

by a slow

of the green

must be within limits 65 to 75% torque

propeller performance

17.1. At the altitude of 500 maximum take-off power.

generator

QFE

during take-off

record the

value of

the

Aug 31/95

LET L 410 UVP-E20 MAINTENANCE SCHEDULE

Check of engine Continuous power.

20.

and

propeller

performance

Maximum

Record the values at the altitude of 2 0 0 0 m.

20.1.

25. Check of oil temperature increase with ice separator vanes in 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.

Check of fuel crossfeed and fuel pumps switching-off

26.

26.1. -

Carry out at the altitude of 4000-5000 m. ~ u r i n gthis check the signaf FUEL PRESSURE- en t h e central warning display -

must not light.

27.

Check of engine operation at idle at V = 200 km/hr I A S

28.

28.1.

power and

Record the values shown at the Maximum Continuous power at the altitude of 5000 m and at idle at V = 200 km/IAS.

27.1.

Maximum Continuous

Check of acceleration within 3 sec

transfer -

of POWER control lever -

Check the acceleration at a slow - at least 3 sec- transfer of POWER control lever at the altitude of 5 0 0 0 m and V = 200 km/hhr IAS.

Aug 3 1 / 9 5

Page 9.2-41

LET L 410 UVP-E20

MAINTENANCE

SCHEDULE

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 run

verification with switched-off fuel pumps; 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.

from idle, continuation of

shifting of

31. In-flight engine starting check

31.1. Carry out at the altitude of 4000 m the following:

carry out the procedure propeller engine shut-down starting the engine

for

manual

feathering

Page 9.2-42

Aug 31/95

LET L 410 UVP-E20

MAINTENANCE

SCHEDULE

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 Check of the response elevator control force.

the

km/hr IAS aeroplane in dependence on

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%, nprop--1800 RPM - 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 MAINTENANCE S C H E D U L E

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 a t t h e 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

MAINTENANCE

SCHEDULE

Course system: liquid compass. When checking the the wiper and fan

deviation switch off

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

MAINTENANCE

SCHEDULE

Stalling speeds - engine idle power Position of wing flaps:

o0 18O 42O

Stalling speed IAS (km/hr)

cruising take-off landing

41. Automatic

feathering

and

automatic

bank control operation

check 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 the straight forward flight with the max. trim deflection with the max. take-off engine power V=200 km/hr IAS with a balanced flight). Increase the flight speed and check the retraction of ABC tab at 205 + - 5 km/hr IAS.

I I

for tab and the

Page 9.2-46

Aug 31/95

LET L 410 UVP-E20

MAINTENANCE

43. Check of

SCHEDULE

operation of ILS, radio and special equipment

altimeter audio switch box

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.

43.1.

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 MAINTENANCE SCHEDULE

44.

Check of fuel transfer from wing tip fuel tanks flight

44.1.

during the

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 MAINTENANCE S C H E D U L E 9.2.4.4.

Program of

acceptance flight test of V

Power setting

510

propeller

To be checked

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/

-in the 3rd to 5th transition n = 2 0 0 0 RPM P

Check of deicing of propeller blades

Aug

31/95

Page

9.2-49

LET L 410 W P - E 2 0

MAINTENANCE

Power setting

SCHEDULE

To be checked

-propeller control lever in position n -enqine congrof lever at take-off power setting.

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

-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.

-speed shall be in tolerance range of + 15 RPM.

ICruise and speed chanqe (by pushing and pulling control column). -altitude 3000 to 2500 m -v = 300 + 40 km/hr - P ~ Lin position n = 1800 l/min -set engine controy lever n = 94 % to 97 % g

-in steady cruise speed n, = 1800 2 10 l/min -at change of speed n, = + 30 l/min.

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

-propeller speed in course of loading and unloading shall be in compliance witk movement of PCL -rea

Aug 31/95

LET L 410 W P - E 2 0 MAINTENANCE SCHEDULE

To be checked

Power setting

Power chanqe -altitude 3000 to 2500 m -v = 300 km/h - P ~ Lin position n, = 1800 l/min -shift ECL from n = 97 % to idle power and back wythin 10 s.

-till steady state (n = 1800 l/min) max. 3 ovgrshoots from the nominal value with tolerance + 30 l/min are permissible. -

Propeller featherinq a/ Automatic feathering -altitude 3000 to 1500 m -v = 190 km/h - P ~ Lin position nv max.

-feathering time 5 s -signal cells on CWD are on

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.

- np

Propeller setting out of feathered position and setting of flight mode -perform in accordance with the Flight Manunal L 410 UVP-E20 aircraft .

setting propeller out of feathered position

time necessary for settins to the feather within 5 s cells on the CWD will be on.

b/ Manual feathering: -altitude 4000 to 1500 m -v = 250 km/h - P ~ Lin position np max.

= max. 20 l/min in clockwise direction

Preparation for feathering -perform in compliance with the Flight Manual L410 UVP-E2C

Aug 31/95

Page 9.2-51

LET L 410 UVP-E20 M2iINTENANCE SCHEDULE

Power setting

To be checked -

After propeller feathering (L.H.)-(R.H.) -v = 300 to 200 km/h hgrizontal ,straight flight without slips

ny = 20 l/min in clockwise direction

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.

setting propeller out of feathered position

- --

Emergency feathering -altitude 4000 to 1500 m -v = 300 km/h - P ~ Lin position nv max.

time for setting to feathered position max. 20 s

After propeller feathering (L.H.)-(R.H.) - v = 3-00 t o 2-00 km/h i-n hBrizantal,straight flight without any slips.

max. 50 l/min in "cYockwlse . direction

Propeller setting out of feathered position and flight mode setting -perform according to the Flight Manual for L410 WP-E20 aircraft.

setting the propeller out of feathered position.

after firts cycle the cell PROPELLER DEICING on CWD goes off.

Feathering -perform according to the Flight Manual for L410 UVP-E20 aircraft. =

Check of deicinq -altitude 100 m QFE to FL 5000m -v = 190 to 350 km/h - P ~ Lin 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

Aug 31/95

LET L 410 UVP-E20 M A I N T E N A N C E SCHEDULE

To be checked

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.

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 stabilization is max. 6 s.

Aborted Landinq -altitude 500 m QFE -v = 180 km/h PCL to position n max. -&t -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.

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 MAINTENANCE S C H E D U L E

Power setting

To be checked

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.

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.

Jheck of propeller unit tiqhtness -after acceptance flight

- 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 4 1 0 UVP-E20 MJiINTENANCE SCHEDULE

May 15/98

Page 9.3-1

Name

Oil

4. Oil

3. Engine oil

No.

GOST 6457-66

MK- 8

Specification (CR)

Specification (CIS)

Application-stated in Supplement 9.1

Application-stated in Supplement 9.1 Aeroshell Compoud MIL-G-16173A

Mutual mixing of oils groups (a,b,c) is not permitted

Note

Aeroshell Turboil 3 DERD 2490, Shell Oil Ensis L, Shell Storage Oil 3.

c) Mobile JET Oil I1 MIL-L 23699 D (USA Exxon Turbo oil 2380, Castrol 599.

b) Aeroshell Turbine OIL 500 (555,560) MIL-L 23699 D (USA DERD.2499 (GB)

Specification (western)

7. Zrease

6. Oil

No.

Name

CIATIM 201 ZOST 6267-74

Specification (CR

CIATIM 201 GOST 2267-74

Specification (CIS)

Note

DEF.STAN 91-51 (GB) AIR 4222 ( France ) NT-10006 (USA) G-382 (NATO)

Equivalent specification:

Mobil Grease 28 Braycote 622, Nycogrease 22 MIL-G-81322. Isoflex LD 318 special A.

Aeroshell Grease 22 or 22 c,

Aeroshell Grease 6 MIL-G-7711 A

Application-stated in Supplement 9.1

ApplicationAeroshell -stated in Fluid 12 Supplement 9.1 MIL-L6085A ESSO Univis P12 MIL-L-6085 A

Specification (western)

MAINTENANCE

Page 9.3-4

SCHEDULE

Jan 12/02

L 4 1 0 UVP-E20 Mi4INTENANCE SCHEDULE

C: 0

-4

U-

-4 't! U -4

U a,

Jan 12/02

Page 9 . 3 - 5

LETECKE ZAVODY a.s. L 410 UVP-E20 M ~ L I N T E N A N C ES C H E D U L E

0 -4

la-

-4 H

'44 U -4

0 Q)

Page 9.3-6

Jan 12/02 R

LETECKE ZAVODY a.s. L 410 UVP-E2O

SCHEDULE

MAINTENANCE

> -I+ C

-4

a c a k m

k a,

c a k m

r l N r n . 4 ' m m m m

4J O

g P t x P t

Jan 12/02 R

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-4

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-4 a)

k -4

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a, Pc

a, C -4 r

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m c

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k a, -

a k m

a o - l o r l

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d 0

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Page 9.3-7

ZAVODY a.s. L 410 UVP-E20 M-AINTENANCE SCHEDULE LETECKE

Page 9.3-8

Jan 12/02 R

LET

L 410 W P - E 2 0 M A I N T E N A N C E SCHEDULE

9.5 List of sealed items

Ser

No.

Component

Location pilot's cockpit.

"FIRE EXT." push-button =overs.

"EMERGENCY LANDING GEAR AND FLAP CONTROL" manual valve.

In p i l o t l s cockpit right control panel.

Emergency static pressure m d total pressure instrument supply valve.

In pilot's cockpit

Maximum contingency power stop.

left control panel.

pilot s cockpit.

Page 9.5-1

LET L 410 WP-E2O

MAINTENANCE

SCHEDULE

Intentionally left blank.

Page 9 . 5 - 2

Aug 3 1 / 9 5

LET L 410 UVP-E2O MAINTENANCE S C H E D U L E

9.6. List of adjustable items

whose adjustment durins service is

prohibited

All instruments and major components on engines, propellers fuel system, hydraulic system and electric and avionic the equipment which are provided with the seal of manufacturer may be adjusted only by the representatives of the manufacturer or persons authorised for t h e adjustment-by the manufacturer. -

I I

NOTE: Permitted adjustment of the LUN 6590.05-8 control unit see MM of the M 601 E or M 601 E-21 engine,

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 MAINTENANCE SCHEDULE

Intentionally left blank.

Page 9.6-2

Aug 31/95

LETECKE ZAVODY a.s. L 410 UVP-E20 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, yearsv1means these items are not subject to overhaul. 9.7.4. The dash that the years.

that

in the column llService life hours-yearsf1 means service life is not limited by flight hours or

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 indicated 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

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

19.7.9.

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

Hose manufacture date

Page 9.7-2

125

Certificate number

X.93

Date of installation in the aircraft

Jan 12/02

LETECKE ZAVODY a.s. L 410 UVP-E20 MAINTENANCE SCHEDULE

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,ntson the data in tables Validity

is given-from the series

e.g. from the 18th series

from the prod. No. of aircraft Pcs set

number of pcs for 1 aircraft number of sets

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

LETECKE ZAVODY a.s. L 410 UVP-E20 MAINTENANCE S C H E D U L E

'ti 4

4J 'ti (d

-4

Page

9.7-4

Jan 12/02

LETECKE ZAVODY a.s. L 410 UVP-E20 MAINTENANCE SCHEDULE

N 0

Jan 12/02

k 0

LO rl

P rl

k 0

Page 9.7-5

LETECKE ZAVODY a.s. L 410 UVP-E20 M Z L I N T E N A N C E SCHEDULE

Page 9.7-6

J a n 12/02

LETECKE ZAVODY a . s . L 410 W P - E 2 0 MAINTENANCE S C H E D U L E

Jan 12/02

Page 9.7-7

LETECKE ZAVODY a . s . L 410 WP-E2O JYUXINTENANCE SCHEDULE

u7 10

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Page 9.7-8

d'd'

a x

trl

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X m m e I

Jan 12/02

No.

hydraulic system (continued)

z ) hoses of

Name of Unit

Effect.

Type /Dwg. No./ Hours

TBO Yrs

Service Life

Time Limits

LETECKE ZAVODY a.s. L 410 UVP-E20

MAINTENANCE

SCHEDULE

u 0 b

m e

k u k m o u l o m

U) U)

iD rl d'd'

k l o k l n o m o m

rl b

m k u l m o m

Page 9.7-10

Jan 12/02

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

m m

k o

m m

S rl In

W d J _

COOm * * U )

k o

0 al

ccl ccl

Jan 1 2 / 0 2

Page 9.7-11

LETECKE ZAVODY a.s. L 410 UVP-E20 MAINTENANCE S C H E D U L E

mno x . . P ~r LC

P Pr4

rl-

Page 9.7-12

~rr

P ri

x '

x rl

n x *

0 m 0rl l rl-

0 rl

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Jan 12/02

c ) hoses of hydraulic system (continued)

Name of Unit Effect.

25HF B 463 979 N (25HF L 410 W P . .4670-244) (without weather radar installation)

Type /Dwg. No./ Hours

TBO Yrs

Hours

Yrs

Service Life

Time Limits

LETECKE ZAVODY a . s . L 410 UVP-E20 MAINTENANCE S C H E D U L E

0 i-i

Z 0

rl-

m d'o u m . * d m I

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Page 9.7-14

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Jan 12/02

4 0

LETECKB

ZAVODY a . s . L 410 UVP-E20 -1NTENANCE SCHEDULE

Jan 12/02

Page 9.7-15

LETECKE ZAVODY a . s . L 410 UVP-E20 MAINTENANCE SCHEDULE

Page 9.7-16

Jan 12/02

LETECKE ZAVODY a.s. L 410 UVP-E20

MAINTENANCE

Jan 12/02

SCHEDULE

Page 9.7-17

LETECKE ZAVODY a . s . L 410 UVP-E20 MAINTENANCE SCHEDULE

Page 9.7-18

Jan 12/02

LETECKE ZAVODY a.s. L 410 UVP-E20 MAINTENANCE S C H E D U L E

m m

Jan 12/02

k o

m m

Page 9.7-19

LETECKE ZAVODY a . s . L 410 UVP-E20 lXLRINTENANCE SCHEDULE

Page 9.7-20

Jan 12/02

LETECKE ZAVODY a.s. L 410 UVP-E20 MAINTENANCE S C H E D U L E

Jan 12/02

Page 9.7-21

LETECKE ZAVODY a . s . L 410 UVP-E20 MAINTENANCE

Page 9.7-22

SCHEDULE

Jan 12/02

MAINTENANCE

SCHEDULE

Okla

a a U I a.rl

Jan 12/02 R

Page 9.7-23

LETECKE ZAVODY a.s. L 410 UVP-E2O MAINTENANCE S C H E D U L E

Page 9.7-24

Jan 12/02 R

LETECKE ZAVODY a.s. L 410 WP-E20 MAINTENANCE SCHEDULE

Jan 12/02

Page 9 . 7 - 2 5

LETECKE ZAVODY a.s. L 410 UVP-E2O M A I N T E N A N C E SCHEDULE

.5 d a,

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E: E 0 PC 2 0 Ptk k U

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Paue 9.7-26

Jan 12/02 R

LETECKE ZAVODY a.s. L 410 UVP-E20 MAINTENANCE SCHEDULE

w' r'l

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Page 9.7-27

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Page 9 . 7 - 2 8

Jan 12/02

LETECKE ZAVODY a . s . L 410 UVP-E20

MAINTENANCE

k 0 rl 0

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a, a, I

m a, I

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53 4 GI

Jan 12/02

SCHEDULE

0 0

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d'd' CV CV

a, 1

I d'

0 0

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P P

CV CV

3 3 4 GI

Page 9.7-29

LETECKE ZAVODY a.s. L 410 UVP-E20 MAINTENANCE S C H E D U L E

c, 0

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1 Page 9.7-30

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Jan 12/02

LETECKE ZAVODY a . s . L 4 1 0 UVP-E20 I?/LAINTENANCE S C H E D U L E

Iel

Jan 12/02 R

Page 9.7-31

Type / D w g . No./ Hours

TBO

CIS CIS CIS

CIS

FKD 5 0 1 DOD

r K D 511 DOD

r K S 2 0 1 DOD

r K S 4 0 1 DOD r K D 1 3 3 DOD o r I'KD 1 3 3 ODL

Contactor

25.

26. C o n t a c t o r

Contactor

24.

27.

28.

CIS

r K D 1 0 3 DOD o r I'KD 1 0 3 ODL

CIS

Contactor

AZR

Hours

23.

Yrs

S e r v i c e Life O r i g i n

C i r c u i t breakers AZRGK

N i n other

Effect.

I n s t r u m e n t s used a l s o chapters :

N a m e of U n i t

22.

S h a p t e r No.

Time L i m i t s

LETECKE ZAVODY a.s. L 410 UVP-E20 M A I N T E N A N C E SCHEDULE

Jan 12/02 R

Page 9.7-33

LETECKE ZAVODY a.s. L 410 UVP-E20 MAINTENANCE SCHEDULE

Page 9.7-34

a f'

Jan 12/02 R

Fire protection

Name of Unit

Pregsure gauge

3. Smoke detector

2. Fire extinguisher

d) Pyrocartridge

c) Pressure gauge

MA16K(from 19th series modify as per Dwg. No. B 580 758 N)

B 067 308 N

b) Discharge head

PPL (8) (Dwg. No. B 067 300 N)

Type /Dwg. No./

72-6600-20

Effect.

a) Bottle

1. Fire extinguisher bottle

No. Yrs

CIS

on condition

Yrs

CIS

20 000

on conditi

Hours

Service Life Origin

on condition

condition

Hours

TBO

Time Limits

LETECKE ZAVODY a . s . L 410 W P - E 2 0 MAINTENANCE S C H E D U L E

rla m

a m

l P l r n

m c n a

G U-l

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Page 9.7-36

Jan 12/02

LETECKE ZAVODY a.s. L 410 UVP-E20

MAINTENANCE

I0 N

Jan 12/02

SCHEDULE

I0 TP

(Val

(Vm

0 0

Page 9.7-37

MAINTENANCE

SCHEDULE

4J G 4 J I O U 40rCr

Page 9.7-38

Jan 12/02 R

LETECKE ZAVODY a . s . L 410 UVP-E20 M2lINTENANCE

Jan 12/02

-0rl

w o w -ZU3

SCHEDULE

Page 9.7-39

LETECKE ZAVODY a.s. L 410 UVP-E20 MAINTENANCE

Page 9.7-40

SCHEDULE

Jan 12/02 R

LUN 1538.XX-8

3. Three-pointer

LUN 1674-8

LUN 1635-8

5. Wing tip tank fuel gauge

6. Fuel gauge

LUN 1637-8

8. Fuel gauge transmitter

LUN 1636.01-8

7. Fuel gauge transmitter

transmitter

LUN 1634.01-8

4. Fuel gauge indicator

indicator

B 562 600 L,P

Type /Dwg. No./

2. Wing tip tank (if installed)

Effect.

0.012 K LUN 1492.01-8

Fuel

Name of Unit

1. Pressure switch

Chapter No. Hours

TBO Yrs

10 000

6 000

8 000

10 000

on conditi

20 000

Hours

Yrs

Service Life

Time Limits

LETECKE ZAVODY a.s. L 410 UVP-E20 MAINTENANCE SCHEDULE

-d

k 5 0 X

(I]

Page 9.7-42

Jan 12/02 R

LETECKE ZAVODY a.s. L 410 UVP-E20 MAINTENANCE SCHEDULE

? C

c, a, k

5 C

k 5 4J a, k

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Page 9.7-43

MAINTENANCE

Page 9.7-44

SCHEDULE

Jan 12/02 R

M2%INTENANCE

Jan 12/02 R

SCHEDULE

Page 9 . 7 - 4 5

LETECKE ZAVODY a.s. L 410 UVP-E20 P&%INTENANCE

Page 9 . 7 - 4 6

SCHEDULE

Jan 12/02 R

MAINTENANCE

Jan 12/02 R

SCHEDULE

Page 9.7-47

LETECKE ZAVODY a.s. L 410 UVP-E20 MAINTENANCE SCHEDULE

Page 9 . 7 - 4 8

J a n 12/02 R

L 410 UVP-E20 MAINTENANCE S C H E D U L E

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LETECKE ZAVODY a.s. L 410 UVP-E20 MAINTENANCE S C H E D U L E

MAINTENANCE

SCHEDULE

C n r l G l r l o r l

Jan 12/02 R

m rl N

Page 9.7-51

LETECKE ZAVODY a . s . L 410 UVP-E20 MAINTENANCE SCHEDULE

P a g e 9.7-52

Jan 12/02 R

LETECKE ZAVODY a.s. L 410 UVP-E2O SCHEDULE

MJlINTENANCE

cll

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Page 9.7-53

LETECKE ZAVODY a.s. L 410 UVP-E20 MAINTENANCE S C H E D U L E

Page 9.7-54

Jan 12/02 R

LETECKE ZAVODY a . s . L 410 UVP-E20 MAINTENANCE SCHEDULE

Jan 12/02 R

f'l

Page 9.7-55

LETECKE ZAVODY a.s. L 410 UVP-E20 MAINTENANCE S C H E D U L E

Page 9.7-56

Jan 12/02 R

LETECKE ZAVODY a.s. L 410 UVP-E2O MAINTENANCE SCHEDULE

Jan 12/02 R

Page 9.7-57

LETECKE ZAVODY a . s . L 410 UVP-E20 MAINTENANCE

SCHEDULE

-4

k k C 0 4J 4J

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Page 9.7-58

Jan 12/02

LETECKE ZAVODY a.s. L 410 UVP-E20 M.AINTENANCE SCHEDULE

U-

cr a

-d

rd a, c, k m

1 C m -d m @ + I

k -4 PI-

Jan 12/02 R

Page 9.7-59

LETECKE ZAVODY a.s. L 410 UVP-E20 MAINTENANCE S C H E D U L E

Page 9.7-60

Jan 12/02 R

LETECKE ZAVODY ass. L 410 UVP-E20 MAINTENANCE S C H E D U L E

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Page 9.7-61

LETECKE ZAVODY a.s. L 410 UVP-E20 MAINTENANCE SCHEDULE

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Page 9.7-62

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032

Zhapter No.

9 ' 00-6/906~06-1 GOODYEAR

550x225 model 4 TUBELESS or

Nose landing gear tyre

Type /Dwg. No./

720x310 model 3 TUBELESS or model 4 TUBELESS or 29~11.0-10/11 OT01-1 GOODYEAR

Effect.

4ain landing year tyre

Nose landing gear uheel

Brake

Main landing gear wheel

Name of Unit

I Hours

9 000 landgs

Hours

Yrs

USA

Service Life Origin

Time Limits

LETECKE ZAVODY a . s . L 410 UVP-E20 M2%INTENANCE

Page 9.7-64

SCHEDULE

J a n 12/02 R

LETECKE ZAVODY a.s.

L 410 W P - E 2 0 M A I N T E N A N C E SCHEDULE

ccl

kc, k

Jan 12/02 R

Page 9.7-65

LETECKE ZAVODY a.s. L 410 UVP-E20

MAINTENANCE

Page 9.7-66

SCHEDULE

Jan 12/02

MAINTENANCE

Jan 12/02

SCHEDULE

Page 9.7-67

am'

head

pressure

Speed signallizer

6. Pitot tube

head

5 . Static pressure

indicator

3. Vertical speed

LUN 1173.XX-8

LUN 1157-7

LUN 1156-7

LUN 1155-7

LUN lb40.XX

LUN 1~113.XX-8

Airspeed indicator

Effect.

LUN 1108.XX-8

Name of Unit

1. ~ i r s ~ e e d indicator

No. Hours

TBO

Yrs

Hours

Yrs

Service Life

Time Limits

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

(I]

0 32

-rl $

J a n 12/02

Page 9 . 7 - 6 9

MAINTENANCE

SCHEDULE

Cl 4J

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b'a

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Page 9 . 7 - 7 0

Jan 1 2 / 0 2 R

I-'

tray )Lighting

b)Encoding I altimeter

Transponder system (if installed)

tray

b)~ n c o d i n g Altimeter

Transponder sydtem (is installed)

USA

set

USA

Origin

2 sets

Time Limits

LETECKE ZAVODY a . s . L 410 UVP-E2O MAINTENANCE SCHEDULE

m 0

Jan 12/02 R

LETECKE ZAVODY a s s . L 410 WP-E20 M2XINTENANCE SCHEDULE

-dd

'ti

a, U

-d

Jan 12/02 R

Page 9 . 7 - 7 3

LETECKE ZAVODY a . s . L 410 UVP-E20 M A I N T E N A N C E SCHEDULE

c, ria,

Page 9 . 7 - 7 4

Jan 12/02 R

MAINTENANCE

SCHEDULE

Oc,

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-4

Jan 12/02 R

rlrl

4 3

Page 9.7-75

LETECKE ZAVODY a.s. L 410 UVP-E20 M A I N T E N A N C E SCHEDULE

Jan 12/02 R

LETECKE ZAVODY a.s. L 410 UVP-E20 MSLINTENANCE

Jan 12/02 R

SCHEDULE

Page 9.7-77

LETECKE ZAVODY a.s. L 410 UVP-E20 MAINTENANCE SCHEDULE

C Q)

O) 4 4

h 0

m Id m QaG Id k - d +J a O)?U

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k 0

Page 9.7-78

aw a-d a-

Jan 12/02 R

MAINTENANCE

SCHEDULE

to I

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EU)

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- 5 cll

Jan 12/02

Page 9.7-79

Power plant

Name of Unit

8 000

P-5 (7:)

Ambient air temperature transmitter

5 000

LUN 5260.XX

1ntGgrated eleotronic limiter unit

cycles

6 750

6 000

Hours

9 000

Yrs

Service Life

or 2 250 cycles

2 000

Hours

TBO

Type /Dwg. No./

LUN 5223-8

Effect .

Time Limits

1. Genkrator speed derivative element

Enqine controls

major components inGtalled on engine )

1. Engine (includinc

No.

LETECKE ZAVODY a.s. L 410 WP-E20 SCHEDULE

MAINTENANCE

Jan 12/02 R

Page 9 . 7 - 8 1

LETECKE ZAVODY a.s. L 410 W P - E 2 0 M A I N T E N A N C E SCHEDULE

Page 9.7-82

Jan 12/02 R

LET L 410 W P - E 2 0 MAINTENANCE SCHEDULE

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:

Average flight

= 60

minutes

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 Flight Flight profile time (min) probability

Pay load

Flight altitude

Runway ratio zoncrete grass

PL .max .

0.8 G

PL .max .

0.8 G

PL max .

.......pay load max.

PL .max . The determined life for the above mentioned average operation is given in the chapter 2. 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 W P - E 2 0

MAINTENANCE

SCHEDULE

Average data for the flight IV.:

Flight time

Flight altitude

200

min.

1.2 km

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 time. Such parts must be preventatively in advance replaced or repaired.

t l I I I I I

The statistics of defects is recorded in a form and submitted to manufacturer of the aircraft for his opinion. The originating defects may following viewpoints

considered

from

the

- defects of common nature (mechanical wear and damage)

I I I I I

occuring

the

average

aircraft. Such defects do not not noted in statistics.

Page

9.9-2

with

other

types

influence the life and are

LET L 410 UVP-E20 MAINTENANCE SCHEDULE

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 the airframe is enclosed in this supplement. Notes for filling-in the defect statistics - number of observed aircraft in the given period single user - only major component are mentioned: fuselage, wing, engine mount, landing-geaF attschnent-fittings horizontal tail sufraces, aircraft controls, wing flaps.

at a

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

SCHEDULE

MAINTENANCE

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

notes : routine maintenance periodic maintenance inspection of aircraft etc.-

during

inspection - one

Page 9.9-4

Aug 31/95

LET

L 410 UVP-E2O MAINTENANCE SCHEDULE

31/95

Page 9 . 9 - 5

LET L 410 W P - E 2 0 M 2 k I N T E N A N C E SCHEDULE

Intentionally left blank

Page

9.9-6

LET L 410 UVP-E20 M A I N T E N A N C E SCHEDULE

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 t h e 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.

9.10.2.

in case of fatigue defects and mechanical damage on primary structural elements of the airframe the repair must be consulted with the aircraft manufacturer.

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

MAINTENANCE

SCHEDULE

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 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 t h e tai-1 u n i t a t 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 W P - E 2 0

JXAINTENANCE

SCHEDULE

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

SCHEDULE

MAINTENANCE

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 W P - E aeroplane in the course of periodic maintenance and inspection. ~esidethe data on the correct dimensions and alignment during the aircraft1s 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 MAINTENANCE S C H E D U L E

9.12.2.2.

~rderinqof 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

MAINTENANCE

SCHEDULE

Intentionally left blank

Page 9.12-4

Aug 31/95