Maintenance Manual Walter m601e, m601e-21

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MAINTENANCE MANUAL

TURBOPROP ENGINE

MODELS

WALTER

M601E

WALTER

M601E-21

MANUAL PART No. 0982055

FOURTH REVISED EDITION

ISSUED JULY 1, 2003

This Manual was approved and signed in Czech by:

Oldřich Matoušek Milan Cibulka

Development Director Civil Aviation Authority

of the Czech Republic

Date: October 30, 2003 Date: December 8, 2003

WALTER a.s.

PRAHA 5 - JINONICE

CZECH REPUBLIC

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G E N E R A L C O N T E N T S

Section 00 INTRODUCTION 00.00.00 INTRODUCTION 1. General 2. Customer Support Dpt. 3. Safety of Work

00.01.00 REVIEW OF INDIVIDUAL SECTIONS

00.02.00 HOW TO USE THIS MANUAL - General

- The concept of dividing this Manual - Revisions

AIRWORTHINESS LIMITATIONS

1. General

2. WALTER M601E and M601E-21 Turboprop Engine Operation Limits 3. Equivalent Cyclic Life (N) of New Critical Parts

Section 5 INSPECTIONS

5.00.00 INSPECTIONS 1. General

5.05.00 TIME BETWEEN OVERHAULS (TBO) 1. Time Between Overhauls (TBO)/Repairs 2. Extension of the TBO

5.10.00 SCHEDULED INSPECTIONS 1. General

2. Review of Individual Scheduled Inspection Types

3. Allowed Replacement of Appliances and Engine Parts During Operation

5.20.00 UNSCHEDULED INSPECTIONS 1. General

2. Unscheduled inspections Section 72 TURBOPROP ENGINE

72.00.00 ENGINE ASSEMBLY, COMPLETE - General

72.01.00 ENGINE LAYOUT AND ITS FEATURES - Description and operation

72.01.01 BASIC TECHNICAL DATA - Description and operation

72.01.02 PERFORMANCE

72.01.03 POWER RATINGS

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72.01.04 ENGINE AND AIRFRAME EQUIPMENT ENSURING ENGINE OPERATION - Description and operation

72.02.00 ENGINE INSTALLATION - Description and operation - Troubleshooting

- Installation and removal - Inspections after installation

- Inspections of the engine instruments fastening

- Inspection of electric installation of the engine instruments - Transportation

- Unpacking of the WALTER M601 engine from a metallic transport container - Engine transportation

72.02.01 PREPARATION FOR THE FIRST ENGINE STARTING - Procedure

72.03.00 OPERATIONAL ABILITY - Description and operation - Troubleshooting

- Engine preheating - Basic operations

- Verifying the parameters - Engine test program - Engine turning

- Turning the generator rotor - Turning the power turbine rotor - Washing the compressor

- Storing of the engine - Engine de-preservation - Installed engine preservation

- Engine preservation for a period up to 30 days

- Engine preservation for a period of 30 days to 3 months - Engine preservation before its removal from the airframe - Preservation of the fuel control system

- De-aerating device installation

72.03.01 TOOLS

- Description and operation

72.09.00 ENGINE PROPER - Description and function

72.10.00 REDUCTION GEAR BOX - Description and function - Troubleshooting

- Servicing

- Replacement of the LUN 133.12-8 propeller speed transmitter

72.11.00 REDUCTION GEAR BOX - Description and function

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72.12.00 COUNTERSHAFT CASING

- Description and function

72.12.01 THE COUNTERSHAFT CASING ASSEMBLY - Description and function

72.12.02 TORQUEMETER SYSTEM - Description and function

72.13.00 THE REDUCTION GEAR BOX OIL SYSTEM - Description and function

- Servicing

72.20.00 AIR INTAKE ASSEMBLY OF THE ENGINE - Description and operation

72.21.00 AIR INTAKE CASING - Description and operation

72.22.00 AIR BAFFLES

- Description and operation - Troubleshooting

- Servicing

- Inspection of engine air baffles

72.23.00 AIR INTAKE PROTECTION - Description and operation - Troubleshooting

- Servicing

- Removal and installation of the intake protective screen - Intake protective screen - inspection

72.30.00 COMPRESSOR

72.31.00 AXIAL COMPRESSOR - Description and operation - Troubleshooting

- Servicing

- Compressor 1st stage rotor blades - inspection

72.31.01 STATOR OF THE AXIAL COMPRESSOR - Description and operation

72.31.02 ROTOR OF THE AXIAL COMPRESSOR - Description and operation

72.31.03 AIR BLEED CASING - Description and operation

72.32.00 CENTRIFUGAL COMPRESSOR - Description and operation

72.32.01 CASING OF THE CENTRIFUGAL COMPRESSOR - Description and operation

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72.32.02 REAR WALL

72.32.03 ROTOR OF THE CENTRIFUGAL COMPRESSOR - Description and operation

72.33.00 ENGINE MOUNTING SYSTEM - Description and operation - Troubleshooting

- Servicing

- M601-907.9 engine mounts - replacement

- The M601-907.9 engine mounts - inspection of the rubber blocks

72.40.00 COMBUSTION CHAMBER - Description and operation

72.41.00 FLAME TUBE

- Detailed visual inspection of flame tubes using endoscope

72.42.00 FUEL SUPPLY

72.43.00 SEALS AND SHIELD - Description and operation

72.50.00 TURBINES

72.51.00 GENERATOR TURBINE - Description and operation

- Detailed inspection of gas generator turbine nozzle guide vane ring using endoscope

- Inspection of gas generator turbine rotor blades using endoscope

72.52.00 POWER TURBINE - Description and operation

- Detailed visual inspection of power turbine blades using endoscope

72.53.00 COOLING AND TEMPERATURE MEASUREMENT - Description and operation

72.60.00 ACCESSORY GEAR BOX - Description and operation - Troubleshooting

- Servicing

- Generator turbine speed transmitter - replacement

72.61.00 ACCESSORY GEAR BOX ITSELF - Description and operation

72.62.00 DRIVE OF ACCESSORIES - Description and operation - Troubleshooting

- Replacement of shaft packing rings of the starter-generator drive, hydraulic pump drive, alternator gear box drive and of the gas generator rotor and propeller speed transmitters drive

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72.63.00 THE ACCESSORY GEAR BOX OIL SYSTEM

72.63.10 OIL TANK

72.63.20 OIL SYSTEM DE-AERATION - Description and operation

72.90.00 EXHAUST SYSTEM - Description and operation

72.91.00 OUTLET DUCT

72.92.00 OUTLET CHANNEL LINER INCLUDING THE CONTAINMENT RING - Description and operation

72.93.00 POWER TURBINE ROTOR SUPPORT ASSEMBLY - Description and operation

Section 73 FUEL SYSTEM

73.00.00 FUEL SYSTEM - General

73.10.00 FUEL SUPPLY SYSTEM - Description and operation - Troubleshooting

- Servicing procedures

73.11.00 FUEL MANIFOLD

- Fuel system - check on tightness

73.12.00 FUEL DRAINAGE

- M601-830.7 drain valve - replacement

73.20.00 FUEL CONTROL SYSTEM - General

- Function

- Function of individual circuits of the fuel control system

73.21.00 FUEL CONTROL UNIT - General

- Description - Troubleshooting - Servicing technology

- FCU de-preservation

- De-aeration of the LUN 6590.05-8 fuel control unit - LUN 6590.05-8 fuel control unit - replacement

- Permitted adjustment of FCU fitted on the engine which can be performed by trained - in personnel of the user

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- Adjustment initial phase of engine starting - Adjustment of the ground idling speed

- Adjustment of the speed controlled by speed governor

- Permitted adjustment of the FCU fitted on the engine which can be performed by personnel of organization appointed to FCU services

- Adjustment in case of slow acceleration up to approximately nG = 90 %

- Adjustment of acceleration in case of in-flight surging in the range of nG =80

to 100 %

- Adjustment in case of slow acceleration above nG = 88 %

- Adjustment of the generator altitude idling speed

- Check on operation of the elastic stop - control element 47 - Adjustment of the emergency circuit

- Adjustment of engine starting by means of adjustment of the pressure difference valve on the automatic starting unit

- Adjustment of the ground idling speed when the possibilities of permissible adjustment by means of elements 40 and 39 have been exhausted

- Adjustment of the fuel flow rate increase at the start of acceleration - Adjustment of the acceleration time

- Adjustment of the generator acceleration - Adjustment of maximum fuel flow

- Procedure in case of acceleration terminated by large overshooting of the generator speed

- Check and adjustment of maximum generator speed by means of the technological stop

- Operations that are allowed to be performed on the FCU - Preservation and storage of the FCU

73.22.00 FUEL PUMP - Description - Troubleshooting - Servicing technology

- De-preservation of the fuel pump

- LUN 6290.04-8 fuel pump - replacement

- Washing and check of the fuel strainer after 300 hours of operation - Operations permitted to be performed on the fuel pump

- Preservation and storage of the fuel pump

- Measures to be taken during breaks in the fuel pump operation 73.30.00 MONITORING INSTRUMENTS

- Description and operation Section 74 IGNITION

74.20.00 IGNITION SYSTEM

- LUN 2201.03-8 low voltage ignition system - Description and operation

- UNISON ignition exciter - General

- Description and operation - Adjustment/Test

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74.21.00 IGNITION UNIT

- LUN 2201.03-8 ignition unit including the spark gap - Description and operation

- UNISON ignition exciter - Description and operation - Troubleshooting

- UNISON ignition exciter - maintenance procedures

- Maintenance of the LUN 2201.3-8 low voltage ignition system - LUN 2201.03-8 ignition system - replacement of

- UNISON 9049765-1 ignition exciter - replacement of

- Making ready the Paltest JT 200 T tester for adjusting and checking the ignition systems

- Maintenance and adjustment of the contact breaker in the LUN 2201.03-8 ignition system

- Test of the 14 UA 41/R discharge gap for the LUN 2201.03-8 ignition system and its adjustment

- Storage, depreservation and overpreservation of LUN 2201.03-8 ignition system 74.22.00 SPARK PLUG

- N25F-3 low voltage spark plug - Description and operation

- CHAMPION CH 34630 spark igniter - Description and operation

- N25F-3 spark plug - Servicing

- CHAMPION CH 34630 spark igniter - Servicing

- Replacement of the low voltage spark plug - Testing the N25F-3 spark plugs

- CHAMPION CH 34630 spark igniter - inspection of 74.23.00 INTERCONNECTING CABLES

- Interconnecting cables for LUN 2201.03-8 ignition system - Description and operation

- Ignition cables - UNISON - Description and operation - Troubleshooting

- Ignition cables - UNISON - Maintenance practices - Check of the interconnecting cables

74.30.00 TORCH IGNITERS

- Replacement of the M601-208.9 igniters 74.31.00 TORCH IGNITER

- Description and operation - Fuel nozzle

74.32.00 FLASH TUBE

- Description and operation 74.40.00 STARTING CYCLE

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Section 75 AIR BLEEDS 75.00.00 AIR BLEEDS

- General

75.20.00 COOLING AND LABYRINTH SEALS CHOKING - Description and operation

75.21.00 AIR FOR ENGINE HOT PARTS COOLING - Description and operation

75.22.00 AIR BLEED FOR LABYRINTH SEALS CHOKING - Description and operation

75.30.00 AXIAL COMPRESSOR AIR BLEED - Description and operation

75.31.00 AIR BLEED VALVE - Description and operation - Troubleshooting

- Servicing technology

- Replacement of the M601-19.4 air bleed valve - The M601-19.4 air bleed valve - washing

- Check of compressor bleed valve function when engine is at rest 75.32.00 AIR BLEED FOR AUTOMATIC CONTROL

75.50.00 AIR BLEED FOR AIRCRAFT NEEDS - Description and operation

Section 76 CONTROL SYSTEM 76.00.00 ENGINE CONTROLS

- General

- Description and operation 76.10.00 POWER CONTROL

- Checking and adjustment of basic position of the engine control lever on the LUN 6590.05-8 FCU

- Checking and adjustment of the „V3“ clearance

- Checking and adjustment of the airframe pull rod length

- Checking and adjustment of the travel of the „BC“ lever of propeller speed governor

- Checking and adjustment of the switching-on/off points of the automatic feathering switch on the engine control lever

- Checking and adjustment of the coincidence of the double-lever mark with the mark on the double-lever bracket

- Adjustment of the fuel shut-off valve actuating lever - Checking and adjustment of the reverse thrust power

- Checking smooth motion and lubrication of ball joints of the engine controls - Lubrication of the automatic feathering switch lever

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76.30.00 SYSTEM OF INTEGRATED ELECTRONIC LIMITERS OF CRITICAL

PARAMETERS

- Purpose, brief technical description and functioning of the system - Operating values of parameters subjected to limitation (calculated) - Troubleshooting

- Inspection of the LUN 1476-8 pressure switch of the torque limiter

- Inspection of the LUN 3280-8 pressure switch of automatic feathering system - Detection of faults - functioning failures - of the system of integrated limiters - Verifying the LUN 5260.04 IELU fault

76.40.00 Checking the function of the system of automatic feathering and rolling

Section 77 INSTRUMENTS FOR MONITORING

77.00.00 ENGINE MONITORING - General

77.10.00 POWER MONITORING INSTRUMENTS - Technology of servicing

77.11.00 THE LUN 1540.02-8 AND LUN 1539.02-8 TORQUE INDICATOR SET TORQUE 0 TO 120 %

- LUN 1540.02-8 torquemeter pressure transmitter - replacement of - LUN 1539.02-8 Torque indicator replacement of

- The LUN 1540.02-8 torque transmitter and the LUN 1539.02-8 indicator revision after 1000 hours

- Calibration of the torque indicator set: LUN 1539.02-8 torquemeter indicator/LUN 1540.02-8 torquemeter transmitter

77.13.00 THE LUN 1333.12-8 INTEGRATED GENERATOR AND PROPELLER SPEED TRANSMITTER

77.15.00 THE LUN 1476-8 TORQUE LIMITER PRESSURE SWITCH - Description and operation

- The LUN 1476-8 torque limiter pressure switch - replacement of - Adjustment of the LUN 1476-8 pressure switch

- Check on adjustment of torque channel

77.20.00 TEMPERATURE MEASURING INSTRUMENTS - Description and operation

- Servicing

77.21.00 LUN 1377-8 INTERTURBINE TEMPERATURE TRANSMITTER - Description and operation

- Interturbine temperature transmitter

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77.22.00 LUN 1358-8 TRANSMITTER OF ELECTRIC RESISTANCE OIL THERMOMETER

- LUN 1358-8 electric resistance thermometer transmitter - replacement of - Inspection of the LUN 1358-8 electric resistance thermometer transmitter

77.40.00 PRESSURE MONITORING INSTRUMENTS - Description and operation

- Servicing

77.41.00 LUN 1559-8/LUN 1559.01-8 FUEL PRESSURE TRANSMITTER - Description and operation

- The LUN 1559-8/LUN 1559.01-8 fuel pressure transmitter - replacement of

77.42.00 LUN 1558-8/LUN 1558.01-8 OIL PRESSURE TRANSMITTER - Description and operation

- LUN 1558-8/LUN 1558.01-8 oil pressure transmitter - replacement of

77.43.00 1.25K LUN 1469.32-8 PRESSURE SWITCH - Description and operation

- Replacement of the 1.25K LUN 1469.32-8 pressure switch (minimum oil pressure signaller)

77.44.00 LUN 1581-8 MINIMUM OIL LEVEL SIGNALLER - Description and operation

- The LUN 1581-8 minimum oil level signaller - replacement of

77.50.00 CRITICAL PARAMETERS LIMITING INSTRUMENTS - Description and operation

- Servicing

77.51.00 LUN 5260.04 INTEGRATED ELECTRONIC LIMITER UNIT - Troubleshooting

- LUN 5260.04 Integrated Electronic Limiter Unit (IELU) - Servicing - The LUN 5260.04 Integrated Electronic Limiter Unit (IELU) - repairs of - Instruction for instruments storage

- Instruments transportation

77.52.00 LUN 3280-8 PRESSURE SWITCH FOR AUTOMATIC PROPELLER FEATHERING

- The LUN 3280-8 automatic propeller feathering pressure switch - replacement of

77.55.00 LUN 5260.02 INTEGRATED ELECTRONIC LIMITER UNIT (IELU) - Description and operation

- The LUN 5260.04 integrated electronic limiter unit - removal and installation of - The LUN 5260.04 integrated electronic limiter unit, adjustment and testing - Integrated electronic limiter unit check using the „TEST“ circuit

- Check on operation of the Integrated Electronic Limiter Unit

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Section 78 EXHAUST SYSTEM

78.10.00 EXHAUST NOZZLES - Description and operation - Troubleshooting

- Exhaust nozzle-replacement of - left M601-418.7

- right M601-419.7

- Exhaust nozzle-visual inspection - Exhaust nozzle repair

- Welding of exhaust nozzle cracks Section 79 _{OIL SYSTEM}

79.00.00 LUBRICATION SYSTEM - Description and operation

79.10.00 ENGINE LUBRICATION SYSTEM - Description and operation

- Troubleshooting

- Engine magnetic plugs - check

- Cleaning and replacement oil filter cartridge. Evaluation of the retained metal abrasive wear.

79.20.00 LUBRICATION SYSTEM MANIFOLDS - Description and operation

- Lubrication system-check on tightness - Engine and accessories - check on tightness

79.30.00 MONITORING INSTRUMENTS - Description and operation

79.40.00 LUBRICATION SYSTEM ADJUSTMENT - Description and operation

79.50.00 OIL FILTERING

- Oil quantity check, oil replenishment

- Filling the engine with oil, lubrication system de-aerating - Engine oil discharging

Section 80 STARTING

80.00.00 STARTING SYSTEM - General

- Engine starting at periodic inspections

- Check of the integrated electronic limiter function (INTEGRATED ELECTRONIC LIMITER UNIT - IELU) - Engine shut down

- Motoring run

80.10.00 ROTATING UP

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80.11.00 STARTER/GENERATOR - Description and operation - Troubleshooting

- Replacement of the LUN 2132.02-8 starter/generator - Test of the LUN 2132.02-8 starter/generator

- Repair of commutator surface by re-turning - Armature removal

- Repair of commutator - Balancing of rotor - Armature installation Section 82 WATER INJECTION

82.00.00 WATER INJECTION - General

82.01.00 REQUIRED PROPERTIES OF WATER - Description and operation

82.20.00 SPRAY RING

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RECORD OF REVISIONS

The date on which new pages have been inserted into the Manual is affixed by the operator. The Bulletin No. is specified only if the revision has been issued as a Bulletin.

REVI- SION No. BULLETIN No. ISSUE DATE OF NEW PAGES

NUMBERS OF AFFECTED SECTIONS INSERTION DATE OF AND SIGNATURE

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REVIEW OF EFFECTIVE PAGES

Section - subsection point Page Date 00 „Record of Revisions“ 1 Jul 1, 2003 2 Jul 1, 2003 00 „Review of

Effective Pages“ 1 Jul 1, 2003 2 Blank Jul 1, 2003 00 „Contents“ 1 Jul 1, 2003 2 Blank Jul 1, 2003 00.00.00 1 Jul 1, 2003 2 Jul 1, 2003 3 Jul 1, 2003 4 Jul 1, 2003 00.01.00 1 Jul 1, 2003 2 Blank Jul 1, 2003 00.02.00 1 Jul 1, 2003 2 Jul 1, 2003 3 Jul 1, 2003 4 Blank Jul 1, 2003 Section - subsection point Page Date

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INTRODUCTION

1. General NOTICE

INFORMATION PRESENTED IN THIS MANUAL, IN ENCLOSED DRAWINGS AND DIAGRAMS IS ASSIGNED FOR DIRECT USE TO PERSONS AND ORGANIZATIONS TO WHOM THIS INFORMATION WAS DELIVERED BY ENGINE MANUFACTURER DIRECTLY OR THROUGH MEDIATORY PERSONS OR ORGANIZATIONS.

FURTHER REPRODUCTION OF DATA PRESENTED IN THIS MANUAL AND THEIR TRANSFER TO OTHER ORGANIZATIONS AND PERSONS IS NOT ALLOWED WITHOUT WRITTEN PERMISSION OF ENGINE MANUFACTURER.

DATA PRESENTED IN THE MANUAL AND ADDITIONAL DATA OBTAINED BY AIRCRAFT OPERATOR ARE NOT ALLOWED TO BE USED FOR OTHER PURPOSE THAN FOR ENGINE MAINTENANCE, PARTS ORDER ETC. IN CONNECTION WITH THE WALTER M601 ENGINE MODELS.

This manual provides information on engine design, function of individual modules, and accessories that should be understood for proper and reasonable maintenance. In addition, procedures are described which could be of advantage as in prevention as in remedy of failures. Therefore this manual gives the schedule and scope of inspections, servicing and operations that should be carried out for reliable and trouble-free operation of the engine.

Maintenance of the WALTER M601 turboprop engines is based on the fact that during the TBO period no maintenance operations are required - except periodic (mostly visual) inspections and minor maintenance. Therefore no heavy maintenance, neither hot parts inspection, etc. is carried out. This is substantiated by endurance testing of the WALTER M601 engines.

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All described maintenance procedures can be carried out in common working environment; no special requirements are imposed on equipment. All necessary tools, aids, spare parts, and consumable material are supplied with the engine.

Nevertheless the described maintenance procedures can be carried out exclusively by qualified personnel, trained-in for the WALTER M601 engine maintenance.

All inspections and maintenance operations must be recorded in Engine Log Book and appliance logs.

Further operations than those described in this manual can be carried out only by personnel fully trained and authorized to technical services.

2. Customer Support Dpt.

Customer Support Dpt. representatives hold contact with customers and airplane operators. Their services are available for rectification of any specific difficulty or problem. Request for contact should be addressed to:

WALTER a.s. Customer Support Dpt. Jinonická 329 150 07 Praha 5 - Jinonice Czech Republic Phone: ++420 25104 2530 Fax: ++420 25721 1430 E-mail: [email protected] Internet http://www.walterengines.com

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3. Safety of Work

Working platforms or stairs are necessary for work on the engine. The personnel must be equipped with antis lip shoes so that the danger of fall will be reduced to minimum.

The following precautions must be respected when washing the engine as installed in the airframe:

- Only washing or lacquer petrol can be used for washing parts where petrol is required. - The airframe must be grounded by connecting a metal part of the undercarriage to

earth.

- Smoking or open fires are forbidden within the distance of 10m. - Fire extinguishing equipment must be ready at the airplane. - Storage batteries must be disconnected.

- No further operations may be carried out - e.g. cleaning the Perspex windows,

- using electric appliances as vacuum cleaners, electric hand drills, etc. Electric hand lamps should be of an explosion-proof model.

- Personnel working with combustibles must be equipped with antistatic shoes and their clothing must not be made of synthetic fibres. Cleaning aids, rags, brushes, etc. must not be made of the synthetic fibres.

- Combustibles must not be poured on concrete floors so that the danger of inflammation caused by the fall of a metal object will be prevented.

- The quantity of cleaning aids in use must be limited to one litre. Cleaning aids must be stored in closed metal containers at least 10 m away from the airplane.

Synthetic oils used for engine lubrication are dangerous to health. In case of stained hands or further parts of the body the stains should be wiped dry immediately; then washed with clean fuel or petrol, followed by washing in warm water with soap.

Basic hygienic principles should also be respected when handling other lubricants, fuels and cleaning aids. Stained skin, respiration of vapour etc. should be prevented. Hands must be washed thoroughly after the work has been finished.

Persons who are not instructed on the procedure related to testing and on results of unqualified or careless behaviour must not attend testing of engines.

It is also strictly forbidden to stay near the propeller.

Prior to engine testing it is necessary to make ready the fire extinguishing equipment. Check the free area in front of and behind the airplane. Inform the attending personnel on the start and on the end of engine test.

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∗ ∗ ∗

CAUTION: AS FAR AS THE NAME OF THE ENGINE MODEL IS PRESENTED ON TABLES OR DIAGRAMS, THESE ARE VALID FOR MARKED MODEL ONLY. IF THE NAME OF ENGINE MODEL IS MISSING, THE TABLES OR DIAGRAMS ARE VALID FOR ALL ENGINE MODELS PRESENTED IN THIS MANUAL.

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REVIEW OF INDIVIDUAL SECTIONS

Section 00 INTRODUCTION AIRWORTHINESS LIMITATIONS Section 5 INSPECTIONS Section 72 ENGINE

Section 73 FUEL SYSTEM Section 74 IGNITION

Section 75 AIR BLEED VALVE Section 76 CONTROLS

Section 77 INSTRUMENTS FOR MONITORING Section 78 EXHAUST SYSTEM

Section 79 OIL SYSTEM Section 80 STARTING

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HOW TO USE THIS MANUAL

GENERAL

The Maintenance Manual has been written in accordance with the USSR Standard GOST 18675-73. It contains a technical description of engine systems subdivided according to their function and operation technology prepared in the form of technological instructions.

In-flight operation of the engine is dealt with in the „Operation Manual“ (Manual Part No. 0982404).

The engine airframe installation is described in detail in the „Installation Manual“ (Manual Part No. 0982502).

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THE CONCEPT OF DIVIDING THIS MANUAL

The Manual is divided into sections that are further divided into subsections and items.

The subdivision is expressed by a numerical index shown in the bottom margin of the page concerned; this index corresponds to the USSR standard.

Example: 72. 10. 00

Section Subsection Item

Engine Reduction gearbox Void

Pages are numbered separately for each subsection. The page number contains also an encoded inner division of every subsection into individual themes; this simplifies orientation and entering of reviews.

Pages are numbered as follows:

General, description and function 1 - 100

Troubleshooting 101 - 200

Servicing technology - general 201 - 300

Standard maintenance in operation 301 - 400

Installation and removal 401 - 500

Adjustment and testing 501 - 600

Inspections and check-ups 601 - 700

Cleaning and painting 701 - 800

Minor repairs 801 - 900

Storing instructions 901 - 1000

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REVISIONS

The revisions in the Maintenance Manual are introduced in the form of replaceable pages always accompanied by a new review of effective pages of the chapter concerned. These are delivered to the users of Manuals together with the „Accompanying List of Revisions”. The user of the Manual is obliged to check whether the pages in his copy conform to the review of effective pages filed at the beginning of each chapter.

Pages not entered in the list must be deleted. The corrected or new page carries a new date of issue.

After having received the revision and inserted it into the manual, the user is required to enter the revision into the „Record of Revisions“ contained in the manual „INTRODUCTION“ and in the beginning of every section, and to add the date and his signature.

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RECORD OF REVISIONS

NUMBERS OF AFFECTED PAGES INSERTION DATE OF AND SIGNATURE

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Section - subsection point Page Date Airworthiness Limitations „Record of Revisions“ 1 Jul 1, 2003 2 Jul 1, 2003 Airworthiness Limitations „Review of

Effective Pages“ 1 Jul 1, 2003 2 Blank Jul 1, 2003 Airworthiness Limitations „Contents“ 1 Jul 1, 2003 2 Blank Jul 1, 2003 Airworthiness Limitations 1 Jul 1, 2003 2 Jul 1, 2003 3 Jul 1, 2003 4 Jul 1, 2003 1 1.7.2003 (in Czech) Section - subsection point Page Date

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AIRWORTHINESS LIMITATIONS

The Airworthiness Limitations section is CAA (Civil Aviation Authority of the Czech Republic) approved and specifies maintenance required under Section 43.16 and 91.403 of the Federal Aviation Regulations and by any applicable airworthiness or operational rule unless an alternative program has been CAA approved.

This chapter was approved and signed in Czech by: Pavel Matoušek,

Director, Airworthiness Division CAA of the Czech Republic

Date: December 8, 2003

1. General

1.1 Engine parts which are exposed to low-cycle fatigue due to cyclic operation of the engine are presented in Table 1.

1.2 Life limits were CAA of the Czech Republic approved within the type certification process. Respecting these limits is therefore mandatory to maintain conformity with approved type design and validity of the airworthiness certification. Changes in part cyclic life limits shall be approved by the CAA of the Czech Republic.

1.3 Airworthiness regulations require operator to record:

a) Consumption of approved number of flight hours in the course of operation in the frame of TBO.

b) Consumption of approved number of equivalent flight cycles in the course of operation in the frame of TBO.

c) Consumption of approved number of years in the course of operation in the frame of TBO.

As far as the operator does not record the number of engine starts, number of take-offs or duration of flights into the Engine Log Book he will be penalized as follows: the missing data will be included in by increased number of engine starts, take-offs or duration of flights as presented in the Table 2 in the section 5.10.00 SCHEDULED INSPECTIONS.

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1.4 The engine manufacturer (or authorized overhaul facility) gives a warranty that all parts assembled in the engine that are subjected to the cyclic load have their life limits (cycles and hours) equal or higher than approved number of hours and cycles for engine operation during further TBO. During this time it is not allowed for operator to disassemble the engine or these parts and to carry out the maintenance of inner parts of the engine.

1.5 If the engine is operated in the way different from the way as supposed in the paragraph 2. WALTER M601E and M601E-21 Turboprop Engine Operation Limits, or the operator supposes that the total allowed time limit for take-off rating will be exceeded or the engine is operated continuously at high ambient temperatures it is necessary to submit the presumed flight cycle to the engine manufacturer for analysis. The manufacturer estimates if new Engine Operation Limits determination is necessary, or not.

2. WALTER M601E and M601E-21 Turboprop Engine Operation Limits

2.1 The No. of equivalent flight cycles is calculated acc. to the following formula: NE = [Ns + AV (Nv - Ns - NP) + AP . NP] . L [1]

where Ns ... No. of engine starts (only starts followed by take-off or several take-offs are considered)

Nv ... No. of take-offs

NP ... No. of take-offs, when the ground idling with propeller in feather position was used before take-off (nG ≥ 60 %; 830 rpm > nV≥ 320 rpm) AV ... abbreviated flight cycles coefficient, i.e. the ground idling speeds of

both gas generator and propeller were used between successive flights (nG ≥ 60 %; nV ≥ 830 rpm)

AP ... abbreviated flight cycles coefficient, when the ground idling speed of gas generator with propeller in feather position was used between successive flights (nG ≥ 60 %; 830 rpm > nV ≥ 320 rpm)

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2.2 Definition of the type flight cycle and the values of the AV, AP a L coefficients:

- for abbreviated flight cycles, i.e. engine idling - take-off - flight - landing with reverse

- engine idling ... AV = 0.56

- for abbreviated flight cycles, i.e. engine idling with propeller in feather position - take-off - flight - landing with reverse - engine idling ... AP = 0.80

- flight mission coefficient ... L = 1.00

For the type flight cycle is considered:

- aborted landing frequency ... 0.05

- time of take-off rating use ... max. 6 % of TBO - average time of one flight cycle ... (60 to 30) min - landing with reverse ... at each landing

The coefficients AV, AP and L for critical parts of the engine necessary for recalculation of abbreviated and complete flight cycles of the WALTER M601E and M601E-21 engines to the equivalent flight cycles in accordance with the formula presented in Para 2.1 are presented in the Table 1.

The Table is used for determination of number of equivalent flight cycles of critical parts at engine overhaul.

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3. Equivalent Cyclic Life (N) of New Critical Parts

Part Description Dwg. No.

Abbreviated Flight Cycle Coefficients Flight Mission Coefficient Equivalent Cyclic Life AV AP L [equiv. cycles] Centrifugal compressor case M601-153.5 M601-154.6 0.58 0.92 11000 Axial compressor drum M601-130.6 0.27 1.03 9900 Impeller M601-1030.7 0.57 0.97 14400 Main shaft M601-1017.7 0.28 1.03 12700

Fuel spray ring M601-2028.4 0.40 0.99 9500

Compressor turbine

disk M601-3335.7 0.37 1.00 10670

Rear shaft M601-3156.9 0.28 1.02 10450

Free turbine disk M601-3220.6 0.66 0.94 0.85 8820 Free turbine shaft M601-4004.7 0.55 0.92 0.85 11100

COEFFICIENTS AV, AP AND L FOR CALCULATION OF EQUIVALENT FLIGHT CYCLES OF CRITICAL PARTS AND THEIR TOTAL EQUIVALENT CYCLIC

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Section - subsection point Page Date 5 „Record of Revisions“ 1 Jul 1, 2003 2 Jul 1, 2003 5 „Review of

Effective Pages“ 1 Jul 1, 2003 2 Blank Jul 1, 2003 5 “Contents“ 1 Jul 1, 2003 2 Blank Jul 1, 2003 5.00.00 1 Jul 1, 2003 2 Blank Jul 1, 2003 5.05.00 1 Jul 1, 2003 2 Jul 1, 2003 3 Jul 1, 2003 4 Jul 1, 2003 5 Jul 1, 2003 6 Blank Jul 1, 2003 5.10.00 1 Jul 1, 2003 2 Jul 1, 2003 3 Jul 1, 2003 4 Jul 1, 2003 5 Jul 1, 2003 6 Jul 1, 2003 Section - subsection point Page Date 5.20.00 1 Jul 1, 2003 2 Jul 1, 2003 3 Jul 1, 2003 4 Jul 1, 2003 5 Jul 1, 2003 6 Jul 1, 2003 7 Jul 1, 2003 8 Jul 1, 2003 9 Jul 1, 2003 10 Jul 1, 2003 11 Jul 1, 2003 12 Jul 1, 2003 13 Jul 1, 2003 14 Blank Jul 1, 2003

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I N S P E C T I O N S

1. General

This Maintenance Manual establishes the plan and scope of inspections of the engine and its accessories. Required inspection activities ensure airworthiness and reliability of engine since start of operation until the overhaul.

All inspection operations have to be carried out by trained and qualified workers, who are approved for servicing engines of the WALTER M601 series and are responsible for quality of their work.

Any inspection has to be recorded in the Engine Log Book and in appliance logs. Definitions:

Overhaul: Engine renovation to the condition when the approved range of operation and life parameters is warranted using inspection, repair or replacement of engine parts in accordance with approved procedure.

Repair: Engine renovation to the condition when the range of operation and life parameters corresponds to the agreement with the customer. Usually the same range of operation hours is to be warranted as at the overhaul, but with smaller number of flight cycles. This condition will be reached using inspection, repair or replacement of engine parts in accordance with approved procedure.

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T I M E B E T W E E N O V E R H A U L S

1. Time Between Overhauls/Repair

The user must send the engine for overhaul/repair to the engine manufacturer (approved repair organization) or to consult with the engine manufacturer the further procedure as far as:

- the number of flight hours in operation exceeds the limit presented in Table 1. Into the flight hours to overhaul/repair is included only the time from beginning of the take-off to the end of landing.

- the number of equivalent flight cycles in operation (calculated from the equation [1], Para 2.1, AIRWOTHINESS LIMITATIONS) exceeds the limits presented in Table 1 or in the Engine Log Book.

- the number of years in operation (with respect to the Para 2. of this section) exceeds the limit presented in Table 1.

Operation Limits to the Overhaul Engines up to S/N 974010 Engines from S/N 981001 Engines from S/N 022001

No. of Flight Hours 2000 3000

No. Equivalent Flight Cycles 2250 3300 6600

No. of Years in Operation 5 *)

*) Extension to 7 years and then to 8 years (max.) is possible on the basis of positive results of engine inspection (ref. 5.05.00, Para 2.a) and Para 2.b)).

OPERATION LIMITS TO THE OVERHAUL Table 1

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NOTE: The engines with elder S/N can be rebuilt to the state beginning from S/N 022001 in accordance with corresponding regulations and the „Overhaul Manual”. The values of cyclic life of critical parts after engine rebuilding are presented in the Engine Log Book. The engines after rebuilding are marked:

- on the engine identification plate by No. 3000 at engines with TBO limits of 3000 flight hours and 3300 equivalent flight cycles.

- on the engine identification plate by No. 3066 at engines with TBO limits of 3000 flight hours and 6600 equivalent flight cycles.

Missing Value Penalty Value Result

τ (flight hours) 3000 hrs at engines up to S/N 974010 _{4000 hrs at engines from S/N 981001} Decreased engine life NS (No. of engine startings) NS = NV NV (No. of take-off) NV = 2 NS NP (No. of take-off after feathering)

NP = NV/2 Decreased cyclic life of critical engine parts NS and NP NS = NV; NP = 0

NV and NP NV = 2 NS; NP = NS NS, NV and NP Full cyclic life of critical parts

is exhausted

All critical parts will be replaced by new ones

INCLUDING OF PENALTY VALUES FOR CALCULATION

OF EQUIVALENT FLIGHT CYCLES AT OVERHAUL WHEN SOME VALUES WERE NOT RECORDED BY THE ENGINE OPERATOR

Table 2

CAUTION: ENGINE MAINTENANCE EXCEEDING PROCEDURES PRESENTED IN THIS MANUAL IS CONSIDERED AS ENGINE OVERHAUL, THAT REQUIRES TO RESPECT THE PROVISIONS PRESENTED IN THE OVERHAUL MANUAL.

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2. TBO Extension

Three options are available to the operator for extending the TBO. They are as follows: a) For engines reaching a calendar time TBO limit before reaching a flight hour TBO limit,

the calendar TBO may be extended by up to two years, to a maximum of seven years from the initial date of TBO (ref. NOTE), by performing the inspection tasks listed in Table 2. The inspection must be performed solely by the authorized personnel.

b) For engines reaching a calendar time TBO limit extended to seven years, the TBO may be extended by one additional year (to a maximum of eight years) by performing the inspection tasks listed in Table 2. The inspection must be performed solely by the authorized personnel.

c) For engines inspected or repaired in accordance with the Manual for Shop Revision at WALTER a.s., the calendar time TBO limit may be extended by a maximum of five years.

NOTE: The initial date of TBO is defined by the manufacturer as follows:

1. For new or overhauled engines delivered by the manufacturer in sealed containers with a nitrogen atmosphere:

a) The initial date of TBO is the date of manufacture or the date of last overhaul (as presented in the Engine Log Book) plus one year, providing the sealed container atmosphere is not impaired, or

b) The date on which the sealed container atmosphere was impaired during the first year of storage.

2. For new or overhauled engines delivered by the manufacturer in short-period preservation, the initial date of TBO is the date of manufacture or the date of last overhaul (as presented in the Engine Log Book).

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REQUIREMENTS FOR CALENDAR TBO EXTENSION WALTER M601E S/N . Customer:

Type of airplane: Matriculation: S/N: Perform the following tasks:

Item Task Finding and Signature

Engine

1. Free Turbine Detailed visual inspection, using an endoscope, for condition of blades (leading and trailing edges, shroud strips) – ref. 72.52.00, Page 601. 2. Gas generator turbine Detailed visual inspection of the nozzle guide

vane ring, using an endoscope – ref. 72.51.00, Page 601.

Detailed visual inspection of the turbine rotor blades, using an endoscope – ref. 72.51.00, Page 602.

3. Combustion

Chamber Detailed visual inspection, using an endoscope, for condition of flame tubes - ref. 72.41.00, Pages 601 to 602.

4. 1st Stage of Axial

Flow Compressor Detailed visual inspection, using an endoscope, for condition of leading edges of the blades in accordance with 72.31.00, Page 601.

For permitted damage – ref. 7231.00, Page 602 to 603.

Engine Accessories and Instruments 5. Compressor Bleed

Valve Functional check of the valve with engine at rest in accordance with Section 75.31.00, Page 407. 6. LUN 2132.02-8

Starter/Generator

Inspection for condition of brushes and commutator in accordance with Section 80.11.00, Page 501.

7. LUN 2201.03-8 Ignition unit

Functional check in accordance with Section 80.21.00, Page 501 (if mounted).

8. LUN 6290.04-8

Fuel Pump Detailed visual inspection of the pump body (corrosion permitted only on non-working surfaces), check/repair of leakage in accordance with Section 73.22.00. Visual inspection of strainer in accordance with Section 73.22.00, Page 601.

9. LUN 6590.05-8 Fuel

Control Unit Detailed visual inspection of the FCU body (corrosion permitted only on non-working surfaces), check/repair of leakage. Check of ground idle speed in accordance with Section 73.21.00, Page 508, max. generator speed in accordance with Section 73.21.00, Page 558, acceleration adjustment in accordance with Section 73.21.00, Page 552, engine starting adjustment in accordance with Section 73.21.00, Page 502.

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Item Task Finding and Signature

10. Oil Filter Oil filter inspection in accordance with Section 79.50.00.

11. LUN 7816-8 Propeller Speed Governor

Detailed visual inspection of the governor body (corrosion permitted only on

non-working surfaces), check of leakage check of governor adjustment, check of slide block clearance in accordance with Propeller Maintenance Manual.

12. Engine Controls

(Kinematic linkage) Detailed visual inspection (corrosion of ball bearings is not permitted), functional check (rubbing of the rope in conduit is not acceptable). Inspection in accordance with Section 76.10.00, Page 601.

13. LUN 1476-8 Torque limiter pressure switch

Check in accordance with Section 76.30.00, Page 601.

14. LUN 1540.02-8 Torque transmitter and LUN 1539.02-8 Indicator set

15. LUN 3280-8 Autofeathering pressure switch

16. Engine Run Engine test run in accordance with Section 72.03.00, Page 501.

Evaluation of engine performance in accordance with Section 72.03.00, Page 501.

Conclusion:

Date: ... Place: ... Signature: ...

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S C H E D U L E D I N S P E C T I O N

1. General

All described scheduled inspections can be carried out in common environs, without further requirements for equipment, in addition to that which is generally supplied with the engine, as well as for consumable material.

2. Review of individual scheduled inspection types

The scope of individual types of inspections is presented in the Table 1.

Scheduled inspection procedures can be distinguished by program and scope into the following types:

A. Inspection Type 1

This inspection type is carried out daily before launching the flight program. The pilot is approved to carry out this type of inspection.

B. Inspection Type 2

After every 100 hrs of operation or every 30 calendar days, whichever comes first. C. Inspection Type 3

Inspection Type 3 is carried out after 300 ±30 hours of flight operation or at the expiry of a period specified by the manufacturer of the individual accessories, whichever comes first.

D. Inspection Type 4

Inspection Type 4 is carried out at the expiry of 900 ±30 hours in flight operation or at the period specified by the manufacturer of the individual accessories, whichever comes first.

NOTE: Each inspection of higher type includes automatically all lower types of inspections.

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Scope of Inspection Inspection Type

1 2 3 4 Check visually fixing of all devices of fuel and oil system; fixing of

starter/generator and parts of ignition set; fixing of alternator.

- x - -

Electrical installation: check on wiring - x - -

Fireseals: check on fixing and cracks - x - -

Compressor inlet protecting screen: check on condition and fixing (ref. 72.23.00 AIR INTAKE PROTECTION).

- x - -

Engine mounts: visual inspection

(ref. 72.33.00 ENGINE MOUNTING SYSTEM)

- x - -

Space inside the nacelle: visual inspection. Check all joints of fuel system on tightness with the booster pump in operation

(ref. 73.11.00 FUEL MANIFOLD).

x x - -

Engine controls: visual inspection for condition. Check full travel of engine control levers incl. possibility to reach the stops on the levers in the cockpit and also on the engine, (ref. 76.10.00 POWER CONTROL)

- x - -

Exhaust nozzles: visual inspection for cracks and deformations. - x - - Chip signallers on the reduction gearbox and accessory drive box

and magnetic plug in oil tank: visual inspection (ref. 79.10.00).

- - x -

PLANNED INSPECTIONS Table 1 (Sheet 1)

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1 2 3 4

Oil system joints and devices: check for tightness (ref. 79.20.00). x x - - Check and replenishment of oil charge in oil tank (ref. 79.50.00). - x - - Check the oil consumption. Should the oil consumption exceed the

approved limit, check the oil system for leakage (ref. 79.20.00).

If trouble persists, proceed as described in 79.10.00.

x - - -

Inspect and rinse the high-pressure fuel filter (ref. 73.22.00 FUEL PUMP).

- - x -

Inspect engine controls as follows:

V3 clearance in engine control linkage; Bc clearance at the propeller governor;

length of the airframe pull rod (ref. 76.10.00 POWER CONTROL).

- - x -

Inspect the condition of all levers, tie rods and ball joints, in the system of engine controls (ref. Inspection/Check, 76.10.00 POWER CONTROL).

- - x -

Inspection and servicing of the torque limiter pressure switch (ref. 76.30.00 SYSTEM OF INTEGRATED ELECTRONIC LIMITERS OF CRITICAL PARAMETERS).

- - - x

Inspection and servicing of the LUN 3280-8 automatic feathering pressure switch.

- - - x

Inspection/check of the torquemeter set

(ref. 77.11.00 THE LUN 1540.02-8 AND LUN 1539.02-8 TORQUE INDICATOR SET TORQUE 0 TO 120 %).

- - - x

Check on adjustment of torque channel (ref. 77.15.00). - - x - Inspection of the oil temperature transmitter (ref. 77.22.00). - - - x

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1 2 3 4

Functional test of the system of limiters (ref. 77.55.00, Pages 601 to 604, IELU check using the „TEST“ CIRCUIT).

- - x -

Check on operation of the IELU (ref. 77.55.00, Pages 605 to 606).

- - x -

Check of LUN 5223 generator speed derivative element (ref. 77.56.00, Pages 601 to 602).

- - x -

Inspection of the oil filter housing in the accessory gearbox; cleaning if necessary. As far as the oil charge is not replaced, the oil filter cartridge must be washed and checked (ref. 79.50.00).

- - x -

Oil charge replacement (ref. 79.50.00). - - x 1)_-

Check the starter/generator for worn brushes (ref. 80.11.00). The grooves of the starter/generator are to be greased with plastic grease AeroShell Grease 6 or Total Specis Cu.

- - x -

Inspection of ignition sets, LUN 2201.03-8 replacement when life limit expired (ref. 74.21.00 IGNITION UNIT).

- - x -

Inspection of igniter plugs N25F-3 (ref. 74.22.00) and Champion CH 34630 (ref. 74.22.00).

- - x -

Check for engine parameters (ref. 72.03.00). - - x -

1)_{First oil charge replacement should be carried out after 300 hours in operation.} The following replacement is to be carried out at each second inspection of type 3 or after 12 months.

At the same time with oil charge replacement the oil filter cartridge is to be replaced.

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3. Allowed Replacement of Appliances and Engine Parts During Operation

If there some failure appears on the appliances or engine parts that cannot be repaired, it is allowed to replace the faulty appliances or engine parts for new ones.

The principle, that the newly installed appliance must cover full remaining engine TBO, must be respected, especially when the used type of appliance can have different TBO. 3.1 The trained user's workers are allowed to replace appliances and engine parts

(delivered by the engine manufacturer by the way of a claim or an order, spare parts 1:1 or 1:10) as follows:

The Way of Verification No. Appliance – Engine Part Without

Verification Ground Engine Test (Full Scale) Ground Engine Test Items 1, 2, 4, 12, 13 Section

1. Fuel Control Unit x

and flight test - 73.21.00 73.10.00 2. Fuel Pump - x - 73.22.00 3. Fuel Manifold - - x 72.03.00 4. Drain Valve - - x 73.12.00 5. Torch Igniter - - x 74.30.00

6. Fuel Pressure Transmitter - - x 77.41.00

7. Oil and Air Manifold - - x 72.03.00

8. Oil Pressure Transmitter - - x 77.42.00

9. Min. Oil Pressure Transmitter - - x 77.43.00

10. Oil Thermometer - - x 77.22.00

11. Oil Filter Cartridge - - x 79.10.00

12. Magnetic Plugs x - - 79.10.00

13. Starter/Generator - - x 80.11.00

14. Ignition Unit - - x 74.20.00

15. Exhaust Nozzles x - - 78.10.00

16. Engine Mounts x - - 72.33.00

17. Integrated Generator and Propeller Speed Transmitter

- x - 72.60.00

72.10.00

18. Protective Compressor Screen x - - 72.23.00

19. Signaller of Min. Oil Quantity - - x 20. Interturbine Temperature

Transmitter

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3.2 Appliances and Engine Parts that can be replaced solely by manufacturer's workers in accordance with internal instructions of the manufacturer:

The Way of Verification No. Appliance – Engine Part Without

Verification Ground Engine Test (Full Scale) Ground Engine Test Items 1, 2, 4, 12, 13 Section

1. Compressor Air Bleed Valve and

Its Control Nozzles - x - 75.31.00

2. Shaft Packing Rings - x - 72.62.00

3. Engine Controls - x - -

4. Automatic Feathering Pressure Switch - - x 77.52.00 5. Air Baffles - - x - 6. Torquemeter Pressure Transmitter - x - 77.11.00 7. Torque Indicator - x - 77.11.00

8. Torque Limiter Pressure Switch - x - 77.15.00

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U N S C H E D U L E D I N S P E C T I O N S

1. General

A. An unscheduled maintenance inspection is carried out when the engine is subjected to unusual stress or operating conditions, exceeds operating limitations or gives unsatisfactory performance.

B. If, as the results of the inspection, engine removal is required, a written report stating the cause of removal in detail (i.e. overtorque, overtemperature, etc.) must be sent with the engine to an overhaul facility.

2. Unscheduled Inspections

A. Table 1 presents the unscheduled maintenance inspections required.

CONDITION ACTION REQUIRED

A. Performance deterioration

OPERATIONAL ABILITY - TROUBLESHOOTING (ref. 72.03.00).

B. Overspeed Check engine/aircraft speed indicating system. If found satisfactory, carry out the following maintenance actions: (1) If gas generator speed exceeded 103 % determine and

rectify cause of overspeed. Remove the engine and send it to an overhaul facility for an overspeed inspection/repair acc. to Overhaul Manual. In case of propeller overspeed proceed acc. to Table 2.

(2) If gas generator rotor speed was more than limits and less then presented in Para (1):

a) Manually rotate gas generator rotor and check for unusual noises.

b) Inspect chip detectors and oil filter cartridge for contamination with metal chips.

Refer to 79.10.00 ENGINE LUBRICATION SYSTEM and 79.30.00 MONITORING INSTRUMENTS. c) Determine and rectify the cause of the overspeed.

UNSCHEDULED INSPECTIONS Table 1 (Sheet 1 of 8)