als365n3rev011en

AS 365AIRWORTHINESS LIMITATIONS

AS 365

VERSION

N3

Issue date : 2003.07.03

Revision 011 frozen : 2009.08.08

Revision issued : 2009.12.17

EUROCOPTERDirection Technique Support

Aéroport International Marseille Provence

13 725 Marignane Cedex FRANCE

00IMPRESDIFF00PGGARDE---2009.08.08---2

AIRWORTHINESS LIMITATIONS

RECORD OF REVISIONS



RECORD OF TEMPORARY REVISIONS



A

EASA Approved AS 365 N3 05-99 APPRO 2009.08.08 Page 1

a

AIRWORTHINESS LIMITATIONS APPROVAL EASA - Approval The Airworthiness Limitations Section is approved and any change must also be approved by The EASA.

Revision 05-99 LOEP Identification Approval Date EASA nb

REV 000 2003.07.03 EASA : 2003.12.19 2307 REV 001 2004.04.02 EASA : 2004.06.22 6472 REV 002 2005.04.07 EASA : 2005.08.30 R.A.01026 REV 003 2005.12.22 EASA : 2006.03.29 R.C.01551 REV 004 2006.04.07 EASA : 2006.07.24 R.C.01832 REV 005 2006.11.14 EASA : 2007.02.28 R.C.02163 REV 006 2007.03.23 EASA : 2007.04.23 R.C.02330 REV 007 2007.04.06 EASA : 2007.04.24 R.C.02031 REV 008 2007.12.14 EASA : 2008.03.17 R.C.02790.R1 REV 009 2008.06.27 EASA : 2008.10.09 R.C.03064 REV 010 2009.01.08 EASA : 2009.03.31 R.C.03380 REV 011 2009.08.08 EASA : 2009.11.16 10027907 REV.1

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LIST OF EFFECTIVE PAGES

N: NewR: RevisedD: Deleted

Chap/Sect Page Type Identification Chap/Sect Page Type Identification

TITLE N 2009.08.0805-99 APPRO 1 N 2009.08.0805-99 LOEP 1 N 2009.08.0805-99 TOC 1 N 2009.08.0805-99 TOC 2 N 2009.08.0805-99 HIGHLIGHTS 1 N 2009.08.0805-99 SB LIST 1 2009.01.0805-99 INTRO 1 2005.04.0705-99 GENE 1 R 2009.08.0805-99 GENE 2 R 2009.08.0805-99 GENE 3 R 2009.08.0805-99 GENE 4 R 2009.08.0805-99 GENE 5 R 2009.08.0805-99 GENE 6 R 2009.08.0805-99 GENE 7 R 2009.08.0805-99 GENE 8 R 2009.08.0805-99 GENE 9 R 2009.08.0805-99 TABLE 1 2008.06.2705-99 TABLE 2 2008.06.2705-99 TABLE 3 2008.06.2705-99-00-REP 1 N 2009.08.0805-99-00 ATA 22-10 1 2003.07.0305-99-00 ATA 25-00 1 2003.07.0305-99-00 ATA 25-63 1 2003.07.0305-99-00 ATA 26-21 1 2005.04.0705-99-00 ATA 53-10 1 2009.01.0805-99-00 ATA 53-10 2 2009.01.0805-99-00 ATA 62-10 1 2007.04.0605-99-00 ATA 62-20 1 2008.06.2705-99-00 ATA 62-20 2 2008.06.2705-99-00 ATA 62-20 3 2008.06.2705-99-00 ATA 62-20 4 2008.06.2705-99-00 ATA 62-20 5 2008.06.2705-99-00 ATA 62-20 6 2008.06.2705-99-00 ATA 62-30 1 2008.06.2705-99-00 ATA 62-30 2 2008.06.2705-99-00 ATA 62-30 3 2008.06.2705-99-00 ATA 62-30 4 2008.06.2705-99-00 ATA 63-10 1 2006.11.1405-99-00 ATA 63-20 1 2009.01.0805-99-00 ATA 63-20 2 2009.01.0805-99-00 ATA 63-20 3 2009.01.08

05-99-00 ATA 63-20 4 2009.01.0805-99-00 ATA 63-30 1 2009.01.0805-99-00 ATA 63-30 2 2009.01.0805-99-00 ATA 63-30 3 2009.01.0805-99-00 ATA 64-21 1 2006.11.1405-99-00 ATA 64-21 2 2006.11.1405-99-00 ATA 64-21 3 2006.11.1405-99-00 ATA 64-21 4 2006.11.1405-99-00 ATA 64-21 5 2006.11.1405-99-00 ATA 65-11 1 2006.11.1405-99-00 ATA 65-21 1 2007.12.1405-99-00 ATA 65-21 2 2007.12.1405-99-00 ATA 65-21 3 2007.12.1405-99-00 ATA 67-30 1 2003.07.0305-99-00 ATA 71-61 1 2003.07.03

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TABLE OF CONTENTS

Title Page

HIGHLIGHTS OF THE REVISION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

1 GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

2 OUTLINE OF THE REVISION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

3 DETAILED DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

3.1 Section 05-99 GENE updated . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

LIST OF SERVICE BULLETINS INCORPORATED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

1 PRESENTATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

2 CLASSIFICATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

05-99 IMPORTANT NOTES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

1 LIMITATIONS SPECIFICATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

2 OCCURENCE REPORTING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

2.1 Reporting to the Airworthiness Authorities . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

2.2 Reporting to the helicopter manufacturer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

3 EFFECTIVITY - RESPONSIBILITY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2

4 LIFE-LIMITED COMPONENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3

4.1 Definition . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3

4.2 In-Service Monitoring . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3

4.2.1 Flight Hours . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4

4.2.2 Centrifugal Load Variation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4

4.2.3 Torque Variation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4

4.2.4 Number of Operations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4

4.3 Airworthiness Limitation Units - Description and Counting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4

4.3.1 Tasks for which the Airworthiness Limitation is Expressed in hours . . . . . . . . . . . . . . . . 4

4.3.2 Tasks for which the Airworthiness Limitation is Expressed in Cycles . . . . . . . . . . . . . . 5

4.3.3 Tasks for which the Airworthiness Limitations are Expressed in Hours AND Cycles 5

4.3.4 Recording . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5

4.4 Removal of Life-Limited Components . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6

4.5 Temporary Limitation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6

5 IDENTIFICATION OF PARTS AND ASSEMBLIES ACCORDING TO AIRCRAFT VERSION . . . . . . 6

5.1 Principle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6

5.2 Specific Version Identification Marking . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6

6 TRANSFER OF A COMPONENT (PART OR ASSEMBLY) INCLUDED IN THE "AIRWORTHINESSLIMITATIONS" CHAPTER FROM ONE AIRCRAFT VERSION TO A DIFFERENT AIRCRAFT

VERSION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6

6.1 Authority to transfer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7

6.2 Application rules . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7

6.3 Calculation Rules . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7

6.4 Counting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9

05-99 HOW TO USE THE TABLES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

1 GENERAL PRESENTATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

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Title Page

2 DESCRIPTION, DOCUMENTATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

3 PART NUMBER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

3.1 Presentation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

3.2 Part Number Cross-References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2

4 TL (TYPE OF LIMIT) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2

5 LIMIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2

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HIGHLIGHTS OF THE REVISION

1 GENERAL

- Check that the content of the sections in accordance with the "List Of Effective Pages" (LOEP).

- Return the acknowledgment card.

2 OUTLINE OF THE REVISION

This revision is coded as follows:

- Revision 011 frozen: 2009.08.08

3 DETAILED DESCRIPTION

3.1 Section 05-99 GENE updated

Paragraph 4 "LIFE-LIMITED COMPONENTS" modified and paragraph 5 "IN-SERVICING

MONITORING" deleted.

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LIST OF SERVICE BULLETINS INCORPORATED

No Frozen revisiondate

Subject Airworthiness directivesNo

01.00.55 08.07.2002 2002-472-057 (A)Tail rotor pitch change control rod05.00.39 23.09.1998 98-384-047 (A)M.R.H - Spherical thrust bearings/ Attach

beams attachment bolts53.00.42 21.02.2001 2001-060-052 (A)Fuselage - 9˚ Frame Latch support53.00.43 21.02.2001 2001-061-053 (A)Fuselage - 9˚ Frame Stretcher support71.00.14 22.03.2000 2000-108-050 (A)POWER PLANT - SAND FILTER -

Checking the system nozzles.05.00.46 07.04.2005 2004-179 (A)Check and replacement of engine fire

extinguishers05.00.48 22.12.2005 2005-182 (A)Check of the MGB planet gear carrier64.00.24 07.04.2005 Not ApplicableTail rotor blade protection against sand

erosion05.00.45 R1 07.04.2006 2006-0101 (A)Check of the Main Gearbox (MGB) Base

Plate (ATA 63-30)05.00.49 R0 14.11.2006 AD-2006-0099Tail Rotor Blade Check (ATA 64-21)62.00.24 R0 23.03.2007 AD-2006-0362-EFrequency Adapter with Ventilation Holes

(ATA 62-20)01.00.59 R0 14.12.2007 AD-2007-0220Tail Rotor Blade Pitch-Control Shafts Part

No. 365A33.6161.20 or 21 (Pre-MOD0765B41 Aluminum Control Shafts) (ATA65-21)

05.00.51 R2 27.06.2008 AD 2006-0321-ECheck of the Bushes and Check forAbsence of Delamination on Starflex StarArm Ends (ATA 62-20)

62.00.23 R0 27.06.2008 AD 2006-0368-ECheck of the Main Rotor Mast Nut (ATA62-30)

05.00.48 R2 08.01.2009 AD 2007-0288-ECheck of the MGB Planet Gear Carrier(ATA 63-20)

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IMPORTANT NOTES

1 LIMITATIONS SPECIFICATION

These limitations may be expressed as:

- A service life limit (SLL): at the expiration of which the component must be scrapped.

- Airworthiness inspection (CHK): performed either periodically or a limited number of times.

NOTE:

When an airworthiness inspection (CHK) requiresa physical measurement (clearance, vibration level,bonding separation surface area, etc.), the valuemeasured at each check must be recorded on asuitable medium (e.g. equipment log card) and kept.

- Miscellaneous specific information.

COMPLIANCE WITH THESE LIMITATIONS ISMANDATORY IN ORDER TO ENSURE THEAIRWORTHINESS OF THE HELICOPTER. THETIME LIMITS (SLL, CHK) MUST NOT BEEXCEEDED AND ANY CHANGE IS SUBJECT TOPRIOR NEGOTIATION WITH BOTH EASA ANDEUROCOPTER.

Refer to the engine manufacturer’s documentation for the airworthiness limitations and life limitsassigned to the engine components.

2 OCCURENCE REPORTING

Reporting of any failure, malfunction, defect or other occurrence which has caused or might havean adverse effect on the continuing airworthiness of the helicopter is a key factor to maintain thehelicopter airworthy and for the continuous improvement of safety.

2.1 Reporting to the Airworthiness Authorities

The operator shall inform his relevant Airworthiness Authorities of each occurrence that shallbe reported according to the local regulation he is subject to.

2.2 Reporting to the helicopter manufacturer

As part of the Continued Airworthiness Program, any technical incident, discovered inoperation or during maintenance work, must be reported by the operator to thehelicopter manufacturer.

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A technical incident is an event with a technical ground and not in accordance withexpectations.

A few examples of technical incidents are given below. This list is not exhaustive. It is only ashort illustrative one, intended to help the operator to understand the definition of a technicalincident that constitutes an occurrence to be reported to the helicopter manufacturer.

In case of doubt on the need to report an event, the event shall be reported.

Examples of incidents to be reported (non exhaustive list):

- difficulty with a technical ground in accomplishing the mission as planned, including but notlimited to difficulty resulting in a mission abort,

- technical event increasing the crew workload,

- technical event that is liable to jeopardize airworthiness for the continuation of the missionor the safety of people onboard or on ground,

- in-flight loss or rupture of any part,

- abnormal damage (wear, scratch, crack, corrosion, delamination, bonding failure,indentation, etc...) to any structural or mechanical part, especially when exceeding the METremoval/repair criteria or in case no maintenance criteria exist,

- system malfunction or loss (including partial or temporary failure) and interferences withinor between systems,

- failure of a system intended to minimize the effect of survivable accidents, including whenbeing used for maintenance or test purpose,

- failure, malfunction of a system, or damage to a part found when complying with anAirworthiness Directive,

- non conformity of a product, part or appliance with its approved design, or of unknown orsuspect origin,

- missing, misleading, incorrect or unclear procedure that could lead to a crew ormaintenance error,

- abnormal vibration,

- abnormal heating, smoke, fire,

- repetitive instances of any technical event which in isolation would not be considered"reportable" but which due to the frequency at which they arise, form a potential hazard,

- ... any other occurrence which has resulted in or may result in an unsafe condition.

In case of doubt on the need to report an event, the event shall be reported.

3 EFFECTIVITY - RESPONSIBILITY

THE LIMITATIONS ASSIGNED TO THE COMPONENT PART NUMBERS LISTED IN THISSECTION ARE APPLICABLE TO COMPONENTS:

- ACQUIRED DIRECTLY FROM EUROCOPTER OR THROUGH THE EUROCOPTERSUBSIDIARIES OR DISTRIBUTION NETWORK.

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- PURCHASED FROM THE EQUIPMENT VENDORS LISTED IN OUR SPARE-PARTCATALOGUES, EITHER DIRECTLY, OR THROUGH THEIR OWN DISTRIBUTION NETWORK.

IN ALL CASES, THE MANUFACTURING SOURCE IS SPECIFIED IN THE "AIRWORTHINESSDOCUMENT" (JAA FORM ONE, EASA FORM ONE OR EQUIVALENT).

EUROCOPTER WILL NOT CARRY OUT REPAIRS ON SERVICE LIFE-LIMITED PARTS WHICHWERE PROCURED OTHER THAN THROUGH THE EUROCOPTER DISTRIBUTION NETWORK.

IT IS PROHIBITED TO REUSE PARTS OR ASSEMBLIES WHICH HAVE BEEN INVOLVED INAN ACCIDENT, WITHOUT FORMAL TECHNICAL APPROVAL FROM THE EUROCOPTERCUSTOMER TECHNICAL SUPPORT DEPARTMENT.

- THE SERVICE LIVES ASSIGNED TO COMPONENTS CONSTITUTE A GUARANTEE FORFLIGHT SAFETY WITH REGARD TO FATIGUE DAMAGE DUE TO FLIGHT LOADS OFCOMPONENTS EXEMPT FROM EXTERNAL DAMAGE. THESE SERVICE LIVES ARE NOT ACOMMERCIAL GUARANTEE AS A COMPONENT MAY BE REMOVED DUE TO WEAR,FRETTING CORROSION, ETC., BEFORE EXPIRY OF THE SERVICE LIFE.

The only warranty applicable to the helicopter and any component is the warranty included in theSales Contract for the helicopter and the components.

Unless otherwise specified, the service lives and airworthiness inspections specified in this"AIRWORTHINESS LIMITATIONS" Section apply to the components whose part numbers arespecified in this Section as well as to their successive dash numbers if these are not yet specifiedin this Section. In this case, check the installation effectivity of the dash number with theEUROCOPTER Customer Support Department.

4 LIFE-LIMITED COMPONENTS

4.1 Definition

Life-limited components are components that are exposed to fatigue damage due to in-servicestress, and whose failure may jeopardize the aircraft safety.

Life-limited components can be damaged by different types of fatigue:

- High-cycle fatigue, which is related to the flight hours logged (very large number oflow-amplitude load variations).

- Low-cycle fatigue, which is related to a small number of large-amplitude load variations(e.g.: centrifugal load variations related to rotor start-up or large torque variations related totakeoff, collective pitch increase).

- Fatigue related to the number of operations of certain components.

The importance of the damage therefore varies with the type of aircraft operation.

4.2 In-Service Monitoring

The airworthiness limitations for a component may be expressed in the one or more of thefollowing units:

- Flight hours (H).

- Cycles of large centrifugal load or torque variations.

- Number of operations (for certain components).

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Some limitations may be defined only for a specific operation.

4.2.1 Flight Hours

Operating hours are counted from takeoff to landing.

4.2.2 Centrifugal Load Variation

To limit the number of parameters to be monitored during aircraft operation, the servicelife limit of the components likely to be damaged by large centrifugal load variations hasbeen calculated based on 5 rotor starting/stopping operations per flight hour.

If aircraft operation involves a mean number of rotor starting/stopping operations greaterthan 5 per flight hour over a period exceeding 500 hours, the actual service life of somecomponents could be smaller than that specified in this document.

In this case, you must advise EUROCOPTER.

4.2.3 Torque Variation

The number of torque variation cycles varies significantly with the multiple missions thatcan be performed by an aircraft (e.g.: External load carrying can involve a very largenumber of torque cycles).

Therefore, no fixed number of cycles has been specified in order to avoid prematureremoval of components that are little exposed to torque variations.

Consequently, the number of torque variation cycles logged must be monitoredcarefully and counted as follows:

1 LANDING WITH OR WITHOUT STOPPING THE ROTOR = 1 CYCLE.

1 EXTERNAL LOAD CARRYING OPERATION = 1 CYCLE.

The cycles related to external load carrying operation must be added to the landingoperation cycles.

4.2.4 Number of Operations

Certain components may be subject to fatigue limitations related to the number ofoperations.

NOTE:

The number of engine failure simulations must be counted on all helicopters fitted with atleast one Arriel 2C engine that has a FADEC system pre Turbomeca modification TU26C.

Engine failure simulations for training purposes have been taken into account on the basisof 125 failure simulations per engine for 1000 flying hours. If this average is exceeded,you should consult the EUROCOPTER Customer Service Technical Support Department.

On all helicopters fitted with 2 Arriel 2C engines, both of which have a FADEC systemthat includes Turbomeca modification TU26C or a later modification, there is no limit asto the number of engine failure simulations for training purposes. The number of enginefailure simulations need not therefore be counted.

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4.3 Airworthiness Limitation Units - Description and Counting

4.3.1 Tasks for which the Airworthiness Limitation is Expressed in hours

Count the hours logged.

E.g.:

63/10/00/000/000/025

FORWARD FLARED COUPLING TUBE

365A35-1010-24 SLL 20000 H

365A35-1010-25

4.3.2 Tasks for which the Airworthiness Limitation is Expressed in Cycles

Count the cycles logged.

E.g.:

63/30/00/000/000/550

MGB BASE

366A32-1060-29 SLL 26100 U

366A32-1060-30

Part: assembly

366A32-1060-29: 366A32-1062-09.

366A32-1060-30: 366A32-1062-10.

4.3.3 Tasks for which the Airworthiness Limitations are Expressed in Hours AND Cycles

Count the hours and cycles logged.

E.g.:

63/20/00/000/000/275

FREEWHEEL SHAFT

365A32-5424-01 SLL 20000 H

// 120000 U

- When an element is affected by several limitations, these are separated by the " // "sign.

4.3.4 Recording

All the components listed in this section must be monitored in service, unless otherwisespecified (Statement "Not to be monitored in service").

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In all cases, in-service monitoring consists in recording the number of appropriate unitson the equipment log card (FME):

- Hours,

- Cycles,

- Hours and cycles.

This individual document is to be created when the component is monitored via the LogCard of its next higher assembly.

These records must include the different assignments of the component, i.e. when thecomponent is transferred from one aircraft to another.

All the documentation must be drawn up to enable recording of all the parameters usedto comply with the service life limit.

4.4 Removal of Life-Limited Components

When the limitation is reached, the component must be removed and retired from service.

When an element is affected by several limitations, it must be removed when a limitation isreached, whichever comes first.

REMINDER

NO MARGINS WITH REGARDS TO THE SHOWN VALUES ARE ACCEPTABLE IN THISCHAPTER.

4.5 Temporary Limitation

The service life limits for which the results of additional fatigue tests indicate the possibility ofan extension, are identified by the statement "Temporary Limitation". The operator shouldtherefore store the component in question after removal, pending the service life extension.

5 IDENTIFICATION OF PARTS AND ASSEMBLIES ACCORDING TO AIRCRAFTVERSION

Generally, components and assemblies can be installed on several versions or types of helicopterin the "DAUPHIN" family. However, operating conditions may differ from one version to the other,and components or assemblies need be identified according to the version to which they havebeen assigned.

Once assigned to an aircraft version, the parts or assemblies mentioned in this Section must beidentified according to the versions on which they have been used.

5.1 Principle

Components are to be identified by indelibly marking one or more letters or digits near thePart Number. This code will be marked in framed capitals.

(Refer to Standard Practices Manual (M.T.C.) Work Card 20.08.05.103).

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Example: X YThe marking (X) first version on which the componentwas installed should be crossed out and (Y) markednext to it.

5.2 Specific Version Identification Marking

Parts or assemblies shall be marked with their specific version identification characters at thelatest during their first removal.

The Log Card of the component in question or of its next higher assembly shall becompleted as soon as the component is installed on the aircraft.

6 TRANSFER OF A COMPONENT (PART OR ASSEMBLY) INCLUDED IN THE"AIRWORTHINESS LIMITATIONS" CHAPTER FROM ONE AIRCRAFT VERSIONTO A DIFFERENT AIRCRAFT VERSION

The transfer of components from/to civil and military aircraft is not authorized.

6.1 Authority to transfer

The transfer of a component (part or assembly) included in the "Airworthiness Limitations"Chapter (1) from a version "x" helicopter to a version "y" helicopter is authorized only if thefollowing three conditions are met simultaneously:

- The helicopter versions "x" and "y" must both be included in the following list of helicoptersfrom the DAUPHIN "family": 365 C, 365 C1, 365 C2, 365 C3, 365 N, 365 N1, 365 N2,365 N3, EC 155 B, EC 155 B1.The installation of a component originating from any other versions or types of helicoptersis strictly prohibited.

- the Part Number of the component to be transferred from helicopter "x" to helicopter "y" islisted both in the "Airworthiness Limitations" Chapter (1) for helicopter "x" and in that forhelicopter "y".

- the component to be transferred does not have a provisional Service Life Limit, either inthe "Airworthiness Limitations" Chapter (1) for version "x" or in that for version "y".

(1) : Section 05.99 for the PRE, Section 04-00-00 for the MSM.

6.2 Application rules

If the transfer is authorized, comply with the following application rules:

6.2.1 If the component Service Life Limits are exactly the same on the aircraft versions "x"and "y", you must continue to count the hours and cycles on the aircraft version "y".

6.2.2 If the component Service Life Limits on the aircraft version "x" and "y" are different,convert the hours and/or cycles already logged by applying the calculation rule given inparagraph 7.3.

6.2.3 When a component which is "not monitored in service" on the aircraft version "x" istransferred to an aircraft version "y" on which it is "monitored in service", this componentshould be considered as new from the time the transfer is effective (operating time in

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hours and/or in cycles equal to zero) (unless this component has already beentransferred as described in paragraph 7.2.4).

6.2.4 When a component is removed from an aircraft version "x" on which it is to bemonitored in service, then installed on the aircraft version "y" on which it is no longer tobe monitored in service, you must continue to monitor this component in service and itsService Life Limit becomes 20000 hours (2) on the aircraft version "y".

The remaining operating time becomes 20000 hours (2) less the equivalent flying time(in accordance with paragraph 7.3).

(2) or the original Service Life Limit if it is greater than 20000 hours.

6.3 Calculation Rules

6.3.1 Elements necessary for the calculations

Calculating the equivalent flying time on aircraft version "y" when the component hasalready flown on aircraft version "x":

Flying time logged on aircraft version "x" = tx.

Component Service Life Limit on aircraft version "x" = SLLx.

Component Service Life Limit on aircraft version "y" = SLLy.

Equivalent flying time on aircraft version "y" = ty.

Operating time still available = T.

6.3.2 Calculation of ty

ty = tx x (SLLy : SLLx).

6.3.3 Calculation of T

Operating time still available: T = SLLy - ty.

NOTE:

This type of calculation is also effective for thecomponents whose Service Life Limit is expressedin cycles.

EXAMPLES:

- Component ‘A’ that has logged 2000 hours on a version N1 aircraft and is transferredto a version N2 aircraft:Service Life Limit of component ‘A’ on version N1: 6000 hours.Service Life Limit of component ‘A’ on version N2: 3000 hours.Equivalent flying time on version N2: 2000 x (3000: 6000) = 1000 hours.Remaining flying time on version N2: 3000 - 1000 = 2000 hours.

- Component ‘B’ that has logged 4000 hours on a version N1 aircraft and is transferredto a version N2 aircraft:Service Life Limit of component ‘B’ on version N1: 8000 hours.Service Life Limit of component ‘B’ on version N2: 10000 hours.

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Equivalent flying time on version N2: 4000 x (10000: 8000) = 5000 hours.Remaining flying time on version N2: 10000 - 5000 = 5000 hours.

- Component ‘C’ that has logged 1800 hours on a version N2 aircraft and is transferredto a version N1 aircraft:Service Life Limit of component ‘C’ on version N2: 2000 hours.Service Life Limit of component ‘C’ on version N1: infinite, not to be monitored inservice.Equivalent flying time on version N1: 1800 x (20000: 2000) = 18000 hours.Remaining flying time on version N1: 20000 - 18000 = 2000 hours.

- Component ‘D’ that has logged 1500 hours on a version N1 aircraft and is transferredto a version N2 aircraft:Service Life Limit of component ‘D’ on version N1: 4500 hours.Service Life Limit of component ‘D’ on version N2: 3000 hours. provisional limitation(no indication authorizing transfer).In this case, the transfer is not authorized.

NOTE:

The above examples can be adapted directly tothe Service Life Limits expressed in cycles byreplacing the word "hours" with the word "cycles"or in example N˚3, by replacing 20000 hours with100000 cycles.

6.4 Counting

6.4.1 Then count the operating hours and/or cycles by adding them to the equivalent flyingtime "ty".

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00IMPRESDIFF00AS 365 N3 05-99 GENE---2009.08.08---10


HOW TO USE THE TABLES

1 GENERAL PRESENTATION

Description, documentation Part Number TL Limit

The components (parts or assemblies) which are subject to an Airworthiness Limitation are listed

according to the ATA 100 Specification (Chapter/Section/Subject).

2 DESCRIPTION, DOCUMENTATION

This column lists the components subject to an Airworthiness Limitations expressed as a Service

Life Limit and/or a checking interval (in which case the applicable document reference is specified).

When different Part Numbers must not be installed together, this fact is specified).

3 PART NUMBER

This column gives the Manufacturer’s Part Number for the component in question.

When applicable, the Illustrated Parts Catalogue (IPC) provides the correlation between the

Manufacturer’s Part Number and the EUROCOPTER identification number (704A....).

The part numbers are also those which are used in all the support publications (MET, IPC, SB,

etc ...) to which a suffix has been allocated. This suffix is used with spares to indicate theinstallation of an Optional Equipment or a specific configuration.

e.g: The limitation given for Part Number 365A32-0200-03 is effective for the

assembly 365A32-0200-03 and the assembly 365A32-0200-03M1.

NOTE:

Certain detail parts listed in this Section are not

procurable (e.g: certain parts built into assemblies

with a TBO).

3.1 Presentation

Components with the same description but with different Part Numbers are identified in the

following way:

ROTOR SHAFT 365A31-4521-00

365A31-4521-01

SLL 1000 H

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3.2 Part Number Cross-References

In the specific case in Section 05.99.00, the maintenance tasks are related to helicopter

safety and airworthiness, and the table below indicates the correlation between theManufacturer’s Part Number and the EUROCOPTER identification number (704A...) for which

only the EUROCOPTER identification number is specified on the log card.

DESCRIPTIONMANUFACTURER’S

PART NUMBER

EUROCOPTER

IDENTIFICATION

NUMBER

ATA 62-20

Spherical thrust bearing 579060

57911100

LB4-1209-2-1

704A33-633-104

704A33-633-212

704A33-633-192

Frequency adapter E1T2624-01A

E1T3023-01

E-4165F01

J-16130-10

J-16130-15

J-16130-22

E4165F11

704A33-640-031

704A33-640-046

704A33-640-088

704A33-640-087

704A33-640-089

704A33-640-099

704A33-640-100

ATA 63.30

Pad laminated

Fitted on assemblies :

578040

579059

E1T2611-21

E1T2611-31

365A38-3020-00

365A38-3020-01

365A38-3020-02

365A38-3020-03

4 TL (TYPE OF LIMIT)

This column is used to specify the type of limitation:

- SLL: Service Life Limit

- CHK: Inspection Check

5 LIMIT

This column specifies:

- The Service Life Limit (SLL) attributed to each component. These limits are expressed in:

Hours (H),

Months (M),

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Years (Y),

Cycles (U).

- The frequency of the periodic and recurring Inspection Checks (CHK). When the InspectionCheck is to be carried out a limited number of times, it is preceded by the letter E.

e.g: E 50 H: the Inspection Check is to be performed once at 50

operating hours.

The limitation(s) specified for the first Part Number are effective for all the other Part Numbers.

Example:

MGB SUSPENSION BAR

ATTACHMENT FITTING

360A21-1326-04

360A21-1326-05

360A21-1326-06

SLL 20 000 H

Several intervals, separated by the sign " // " are assigned to certain operations. When this is thecase, the corresponding maintenance action must always be carried out at the first limit reached

(flying hours, number of cycles, number of utilizations, calendar time ...).

-ALF: The operation must be carried out After the Last Flight of the dayirrespective of the number of flying hours logged.

-ALF // 10 H: The operation must be carried out After the Last Flight of the day

without exceeding the number of flying hours indicated (unlessotherwise specified).

Example :

SPHERICAL THRUST BEARING ALL MP/N CHK ALF

// 10 H

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00IMPRESDIFF00AS 365 N3 05-99 TABLE---2008.06.27---4


05-99-00-AIRWORTHINESS LIMITATIONS

Chap/Sect Description Page

22-10 . . . . . . . . . . . . . . . . . . . . . . . . OPT - DETECTION, TRIM, ACTUATOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

25-00 . . . . . . . . . . . . . . . . . . . . . . . . EQUIPMENT AND FURNISHING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

25-63 . . . . . . . . . . . . . . . . . . . . . . . . OPT - ELECTRICAL HOIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 126-21 . . . . . . . . . . . . . . . . . . . . . . . . ENGINE FIRE EXTINGUISHING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

53-10 . . . . . . . . . . . . . . . . . . . . . . . . PRIMARY STRUCTURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 162-10 . . . . . . . . . . . . . . . . . . . . . . . . MAIN ROTOR BLADES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

62-20 . . . . . . . . . . . . . . . . . . . . . . . . MAIN ROTOR HEAD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

62-30 . . . . . . . . . . . . . . . . . . . . . . . . MAIN ROTOR MAST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 163-10 . . . . . . . . . . . . . . . . . . . . . . . . ENGINE/MGB COUPLING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

63-20 . . . . . . . . . . . . . . . . . . . . . . . . MAIN GEARBOX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

63-30 . . . . . . . . . . . . . . . . . . . . . . . . SUPPORTS AND ATTACHMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 164-21 . . . . . . . . . . . . . . . . . . . . . . . . TAIL ROTOR HEAD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

65-11 . . . . . . . . . . . . . . . . . . . . . . . . TAIL ROTOR DRIVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

65-21 . . . . . . . . . . . . . . . . . . . . . . . . TAIL GEARBOX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 167-30 . . . . . . . . . . . . . . . . . . . . . . . . SERVO-CONTROL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

71-61 . . . . . . . . . . . . . . . . . . . . . . . . OPT - SAND FILTER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

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00IMPRESDIFF00AS 365 N3 05-99 REP---2009.08.08---2

Description, documentation Part number TL LIMIT


ATA 53-10

53-10 PRIMARY STRUCTURE

53/10/00/000/000/000

TRANSMISSION DECK - FWD MGB FITTINGSLL 20000 H365A21-3354-02

365A21-3354-03

365A21-3354-04365A21-3354-05

53/10/00/000/000/020

TRANSMISSION DECK - AFT MGB FITTINGSLL 20000 H365A21-3355-02

365A21-3355-03

365A21-3355-04

365A21-3355-05

53/10/00/000/000/040

TRANSMISSION DECK - MGB SUSPENSION FITTINGSLL 20000 H360A21-1326-04

360A21-1326-05360A21-1326-06

53/10/00/000/000/050

CARBON TUBE - TGB MOUNTSLL 20000 H365A23-4210-00

365A23-4210-02

53/10/00/000/000/055

CARBON TUBE - TGB MOUNTSLL 30000 H365A23-4211-00

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ATA 53-10

53/10/00/602/000/070

9˚ FRAME (LATCH SUPPORT)CHK 550 H

MET 53.10.00.602

PARA. 3.4

Check to be carried out on helicopters:

- that left the works before October 15, 2000and on which edge distance on at least one

hole is less than 8 mm.

- POST MOD 0753B31 or SB 53.00.20.- BEFORE REPAIR 365A094158 or REPAIR SHEET

53.02.00A.Repair 365A094158 complies with the

instructions given in para. 2B2 of

ASB 53.00.42.

53/10/00/602/000/080

9˚ FRAME (STRETCHER SUPPORT)CHK 550 H

MET 53.10.00.602

PARA. 3.5

Check to be carried out from 5300 flight hours

on aircraft:- that left the works before January 31, 2001

and on which edge distance on at least one

hole is less than 5 mm.- BEFORE REPAIR 365A094159.

Repair 365A094159 complies with the

instructions given in para. 2B2 ofASB 53.00.43.

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ATA 62-20

62-20 MAIN ROTOR HEAD

62/20/00/000/000/030

MAIN ROTOR HUBCHK 100 H365A31-0012-02

365A31-0012-03

MET 62.20.00.601

PARA. 3.B

Check.

62/20/00/000/000/075

LOWER ATTACH BEAMSLL 4400 H365A31-1850-04

62/20/00/000/000/097

UPPER ATTACH BEAMSLL 4400 H365A31-1850-05

62/20/00/000/000/115

SPHERICAL THRUST BEARINGCHK 10 HALL MP/N

MET 05.21.00.603

PARA. 14.4

Check the elastomer section.

62/20/00/000/000/120

SPHERICAL THRUST BEARINGSLL 1000 H704A33-633-076

These parts cannot be installed on the sameaircraft as parts with other MP/N.

Service life limit for the metal section only.

62/20/00/000/000/130

SPHERICAL THRUST BEARINGSLL 2400 H579060

These parts cannot be installed on the same

aircraft as parts with other MP/N.


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ATA 62-20

62/20/00/000/000/140

SPHERICAL THRUST BEARINGSLL 3500 HLB4-1209-2-1

These parts cannot be installed on the sameaircraft as parts with other MP/N.


62/20/00/000/000/141

SPHERICAL THRUST BEARINGSLL 3500 H57911100

These parts cannot be installed on the same

aircraft as parts with other MP/N.


62/20/00/000/000/143

FREQUENCY ADAPTER

E1T2624-01A

E1T3023-01365A31-1019-22

365A31-1019-23

Frequency adapters:

- P/N E1T2624-01A or 365A31-1019-22manufactured before the 2nd quarter 1991

with a S/N lower than 8188.- P/N E1T3023-01 or 365A31-1019-23

manufactured before the 2nd quarter 1991

with a S/N lower than 3122.must not be installed.

62/20/00/000/000/148

FREQUENCY ADAPTERCHK 10 HE4165F11

J-16130-22

MET 05.21.00.603

PARA. 14.3

Hot climatic conditions and/or tropical anddamp atmosphere.

Check that the holes are not bloked.

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ATA 62-20

62/20/00/000/000/152

FREQUENCY ADAPTERCHK 10 HE-4165F01

E1T2624-01AE4165F11

J-16130-10J-16130-15

J-16130-22

365A31-1019-22365A31-1019-24

365A31-1019-25

365A31-1019-26MET 05.21.00.603

PARA. 14.3

These adapters cannot be installed on the sameaircraft, nor with adapters with other MP/N.


62/20/00/000/000/165

FREQUENCY ADAPTERCHK 10 HE1T3023-01

365A31-1019-23

MET 05.21.00.603

PARA 14.3

These adapters cannot be installed on the same

aircraft, nor with adapters with other MP/N.Only adapters with serial No. not less than

M202 can be installed.


62/20/00/000/000/169

FREQUENCY ADAPTERCHK 10 H365A31-1019-22

365A31-1019-23365A31-1019-24

365A31-1019-25

365A31-1019-26MET 05.21.00.603

PARA. 14.3

Hot climatic conditions and/or tropical anddamp atmosphere.

Check that the holes are not blocked.

Check that the lockwire is in place.

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ATA 62-20

62/20/00/000/000/170

ROTOR BLADE PINSLL 20000 H365A31-1771-20

62/20/00/000/000/180

ROTOR BLADE PINSLL 6100 H365A31-2031-20

365A31-2031-21

Temporary limit.

62/20/00/000/000/190

BLADE HORNSLL 20000 H365A31-1998-02

For blade horns with serial number less than

100000, only those whose MP/N is followed bythe letter X can be installed.

62/20/00/000/000/200

SPHERICAL THRUST BEARING - ATTACH BEAM PINSLL 1000 H365A31-1898-20

62/20/00/000/000/210

SPHERICAL THRUST BEARING - ATTACH BEAM PINSLL 1500 H365A31-1970-21

Temporary limit.

62/20/00/000/000/215

SPHERICAL THRUST BEARING - ATTACH BEAM PINCHK 550 H365A31-1898-20

365A31-1970-21

MET 62.20.00.601

PARA. 3.C.4.1

Tightening torque load check.

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ATA 62-20

62/20/00/000/000/220

FREQUENCY ADAPTER - ATTACH BEAM PINSLL 4200 H365A31-1886-20

365A31-1886-21

62/20/00/000/000/245

STARFLEX STARCHK ALF

// 10 H

ALL MP/N

MET 05.21.00.603

PARA. 14.5

Check.

62/20/00/000/000/255

STARFLEX STARSLL 1000 H365A31-1708-00

365A31-1708-01

62/20/00/000/000/261


Involves the installation of swivel bearings

704A33-633-124.

62/20/00/000/000/266


365A31-1708-04

Involves the installation of swivel bearings704A33-633-124.

62/20/00/000/000/275


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ATA 62-20

62/20/00/000/000/285


365A31-1810-02365A31-1810-03

365A31-1810-04


62/20/00/000/000/310



62/20/00/601/000/016

STARFLEX STARCHK 10 H365A31-1210-00

365A31-1708-00

365A31-1708-01365A31-1708-02

365A31-1708-03

365A31-1708-04365A31-1810-00

365A31-1810-01

365A31-1810-02365A31-1810-03

365A31-1810-04

MET 62.20.00.601

PARA. 3.A.4

Visual check of the adhesive bead on the bushes

and check for absence of delamination on theStarflex star arm ends.

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ATA 62-30

62-30 MAIN ROTOR MAST

62/30/00/000/000/055

ROTOR MASTCHK 1650 H365A31-0002-05

MET 62.30.00.601

PARA. 3.K.1

Check the nut.

62/30/00/000/000/100

SWASHPLATE BEARINGCHK 100 H

MET 12.00.00.313

PARA. 2.1

POST MOD 0762B42 or 0762B43.

Greasing.

62/30/00/000/000/110

SWASHPLATE BEARINGCHK 500 H

MET 12.00.00.313

PARA. 2.2

POST MOD 0762B42 or 0762B43.

Greasing.

62/30/00/000/000/152

NON-ROTATING SWASHPLATESLL 20000 H365A31-1101-06

365A31-1101-07365A31-1101-09

365A31-1101-12

365A31-1101-13365A31-1101-14

365A31-1101-15

365A31-1101-16365A31-1101-18

62/30/00/000/000/155

NON-ROTATING SWASHPLATESLL 20000 H365A31-1101-17

AS 365 N3 05-99-002008.06.27 ATA 62-30 Page 1

EASA Approved



ATA 62-30

62/30/00/000/000/160

ROTATING SWASHPLATESLL 20000 H365A31-1100-04

365A31-1100-05

62/30/00/000/000/172

PITCH-CHANGE RODCHK 10 HALL MP/N

MET 05.21.00.603

PARA. 14.2

Check.

62/30/00/000/000/175

PITCH-CHANGE RODSLL 20000 H365A31-1122-20

365A31-1122-21

62/30/00/000/000/190

ROTOR MAST-HUB ATTACHMENT BOLTSLL 1000 H365A31-1182-20

365A31-1182-21

365A31-1183-20365A31-1183-21

MP/N 365A31-1182-20/21 (this bolt can be

installed on aircraft equipped with blade

folding system).

62/30/00/000/000/200

INNER BEARING STOPSLL 20000 H365A31-1085-21

365A31-1085-22

62/30/00/000/000/210

OUTER BEARING STOPSLL 20000 H365A31-1105-21

365A31-1105-22

AS 365 N3 05-99-002008.06.27 ATA 62-30 Page 2

EASA Approved



ATA 62-30

62/30/00/000/000/220

LOWER SCISSORS LINKSLL 20000 H365A31-1116-01

365A31-1116-03365A31-1116-04

62/30/00/000/000/230

UPPER SCISSORS LINKSLL 20000 H365A31-1115-01

365A31-1115-03

365A31-1115-04

62/30/00/000/000/250

SCISSORS PINSLL 5000 H365A31-1175-20

365A31-1175-21

62/30/00/000/000/290

SCISSORS DRIVESLL 20000 H365A31-1171-00

62/30/00/000/000/305

FLARED HOUSINGSLL 20000 H365A31-2101-07

365A31-2101-09

365A31-2101-10

62/30/00/000/000/315

ROTOR MAST BEARING SPACERSLL 1700 H365A31-1106-01

365A31-1106-02

62/30/00/000/000/325

ROTOR MAST BEARING SPACERSLL 6000 H365A31-1178-00

AS 365 N3 05-99-002008.06.27 ATA 62-30 Page 3

EASA Approved



ATA 62-30

62/30/00/000/000/420

ROTOR SHAFTSLL 12000 H

// 60000 U

365A31-1179-05

AS 365 N3 05-99-002008.06.27 ATA 62-30 Page 4

EASA Approved



ATA 63-20

63-20 MAIN GEARBOX

63/20/00/000/000/020

SERVOCONTROL ATTACHMENT FITTINGSLL 20000 H360A32-1163-01

360A32-1163-02

63/20/00/000/000/030

SERVOCONTROL ATTACHMENT FITTINGSLL 8000 H360A32-1163-03

360A32-1163-04

63/20/00/000/000/055

CASINGSLL 20000 H365A32-2046-08

365A32-2046-10

365A32-2046-11365A32-2046-12

365A32-2046-14

365A32-2046-16365A32-2049-07

365A32-2049-08365A32-2049-16

365A32-2049-17

63/20/00/000/000/058

PLANET GEAR CARRIERCHK 50 H360A32-3036-20

360A32-3036-21

MET 63.20.00.608

Borescope inspection.

63/20/00/000/000/060

PLANET GEAR CARRIERSLL 36000 U360A32-3036-20

63/20/00/000/000/062

PLANET GEAR CARRIERSLL 36000 U360A32-3036-21

AS 365 N3 05-99-002009.01.08 ATA 63-20 Page 1

EASA Approved



ATA 63-20

63/20/00/000/000/095

TAIL ROTOR DRIVE SHAFT BEVEL GEAR WHEELSLL 13000 H365A32-1058-21

365A32-1058-22

63/20/00/000/000/115

TAIL ROTOR DRIVE SHAFT BEVEL PINIONSLL 3700 H360A32-1029-23

360A32-1029-24360A32-1029-26

360A32-1029-27360A32-1029-28

360A32-1029-29

Part: assembly

360A32-1029-23: 360A32-1218-03.360A32-1029-24: 360A32-1218-04.

360A32-1029-26: 360A32-1218-06.360A32-1029-27: 360A32-1218-07.

360A32-1029-28: 360A32-1218-08.

360A32-1029-29: 360A32-1218-09.

63/20/00/000/000/123

FIXED FLANGE (REAR OUTPUT)SLL 9500 H360A32-2034-20

360A32-2034-21360A32-2034-22

360A32-2034-23

63/20/00/000/000/125

TAIL ROTOR DRIVE SHAFT FLANGESLL 20000 H360A32-1035-20

360A32-1035-21

63/20/00/000/000/130

MAIN BEVEL GEAR WHEELSLL 20000 H360A32-3256-24

AS 365 N3 05-99-002009.01.08 ATA 63-20 Page 2

EASA Approved



ATA 63-20

63/20/00/000/000/135

MAIN BEVEL GEAR WHEELSLL 20000 H360A32-3256-25

360A32-3256-26

63/20/00/000/000/160

FIRST REDUCTION PINIONSLL 20000 H365A32-4129-03

63/20/00/000/000/180

DOUBLE PINIONSLL 20000 H365A32-4022-22

365A32-4022-23

365A32-7100-20

63/20/00/000/000/230

FIXED RING GEARSLL 20000 H365A32-7035-20

63/20/00/000/000/260

VERTICAL SUN GEAR SHAFTSLL 20000 H365A32-7021-20

63/20/00/000/000/266

VERTICAL SUN GEAR SHAFTSLL 20000 H365A32-7021-22

365A32-7021-23

63/20/00/000/000/275

FREEWHEEL SHAFTSLL 20000 H

// 120000 U

365A32-5424-01

AS 365 N3 05-99-002009.01.08 ATA 63-20 Page 3

EASA Approved



ATA 63-20

63/20/00/000/000/320

PLANET GEARSLL 20000 H365A32-7023-20

365A32-7023-21

Part: assembly

365A32-7023-20: 365A32-7700-00/01/02.

365A32-7023-21: 365A32-7700-03/04,

365A32-9011-00,

365A32-9013-00.

63/20/00/000/000/341

FIRST REDUCTION GEAR CASINGSLL 20000 H365A32-7108-00

63/20/00/000/000/355

MGB - ELECTRICAL OR NON-ELECTRICAL MAGNETIC PLUGCHK 10 HALL MP/N

MET 12.00.00.601

Check.

63/20/00/000/000/525

HALF-GIMBAL JOINTSLL 20000 H365A32-7110-00

365A32-7112-00

63/20/00/000/000/545

GIMBAL JOINT RINGSLL 20000 H365A32-7114-00

365A32-7114-01

AS 365 N3 05-99-002009.01.08 ATA 63-20 Page 4

EASA Approved



ATA 63-30

63-30 SUPPORTS AND ATTACHMENTS

63/30/00/000/000/053

MGB SUSPENSION BAR FORWARD RH OR AFT LHSLL 20000 H365A38-0130-01

Part: assembly

365A38-0130-01: 365A38-0130-01-01,

365A38-0130-11.

63/30/00/000/000/054

MGB SUSPENSION BAR FORWARD LH OR AFT RHSLL 20000 H365A38-0130-02

Part: assembly365A38-0130-02: 365A38-0130-12.

63/30/00/000/000/055

MGB SUSPENSION BAR FORWARD RH OR AFT LHSLL 20000 H365A38-0130-03

Part: assembly365A38-0130-03: 365A38-0130-13.

63/30/00/000/000/070

MGB SUSPENSION BAR FORWARD LH OR AFT RHSLL 20000 H365A38-0130-00

Part: assembly365A38-0130-00: 365A38-0130-00-01,

365A38-0130-10.

63/30/00/000/000/105

MGB SUPPORT DIAGONAL CROSS-MEMBERSLL 20000 H365A38-3062-20

AS 365 N3 05-99-002009.01.08 ATA 63-30 Page 1

EASA Approved



ATA 63-30

63/30/00/000/000/116

MGB SUPPORT BARCHK 50 H365A38-3014-02

MET 63.30.00.601

PARA. 3.A.1

Check.

63/30/00/000/000/137

MGB SUPPORT BARSLL 3000 H365A38-3014-02

63/30/00/000/000/160

MGB SUPPORT BARSLL 1000 H365A38-3045-00

63/30/00/000/000/190

MGB SUSPENSION SUPPORTSLL 20000 H365A38-3046-00

365A38-3046-01

63/30/00/000/000/210

LAMINATED STOPCHK 100 HE1T2611-21

E1T2611-31

579040579059

MET 63.30.00.601

PARA. 3.B.1

These MP/NS cannot be mixed together.

Not to be monitored in service.

63/30/00/000/000/550

MGB BASESLL 26100 U366A32-1060-29

366A32-1060-30

Part: assembly366A32-1060-29: 366A32-1062-09.

366A32-1060-30: 366A32-1062-10.

AS 365 N3 05-99-002009.01.08 ATA 63-30 Page 2

EASA Approved



ATA 63-30

63/30/00/000/000/560

MGB BASECHK 55 H366A32-1060-26

MET 63.30.00.601

PARA. 3.H.1

Part: assembly

366A32-1060-26: 366A32-1062-06.Operation to be performed from 7300 operating

cycles of the new MGB or when the MGB has

already been subjected to overhaul orreconditioning.

Check.

AS 365 N3 05-99-002009.01.08 ATA 63-30 Page 3

EASA Approved

00IMPRESDIFF00AS 365 N3 05-99-00---ATA 63-30---2009.01.08---4



ATA 65-21

65-21 TAIL GEARBOX

65/21/00/000/000/000

CENTER CONTROL SPIDERSLL 20000 H365A33-2033-20

65/21/00/000/000/010

CENTER CONTROL SPIDERSLL 20000 H365A33-6112-00

365A33-6112-01

65/21/00/000/000/025

INPUT PINIONSLL 9100 H365A33-6123-22

365A33-6123-24

65/21/00/000/000/030

BEVEL GEAR WHEELSLL 20000 H365A33-6104-00

365A33-6104-01365A33-6104-02365A33-6104-03

65/21/00/000/000/055

SLIDING FLANGESLL 9400 H365A33-6197-21

365A33-6197-22

65/21/00/000/000/065

INPUT FLANGESLL 12800 H365A33-6196-21

365A33-6196-22365A33-6196-23365A33-6196-24

AS 365 N3 05-99-002007.12.14 ATA 65-21 Page 1

EASA Approved



ATA 65-21

65/21/00/000/000/080

CONTROL ROD

365A33-6161-20365A33-6161-21

Control rod not-airworthy.

65/21/00/000/000/086

CONTROL RODSLL 20000 H365A33-6214-20

65/21/00/000/000/106


65/21/00/000/000/108


65/21/00/000/000/115

INPUT CASINGSLL 20000 H365A33-6128-00

365A33-6128-01

For blades on which the optional OP61B33 hasbeen embodied, should one or more polyurethaneprotective plates be lost, each flying hourlogged without a protective plate shall becounted double.

65/21/00/000/000/120

CASINGSLL 20000 H365A33-6137-02

365A33-6137-03

AS 365 N3 05-99-002007.12.14 ATA 65-21 Page 2

EASA Approved



ATA 65-21

65/21/00/000/000/135

FLARED COUPLING TUBESLL 20000 H365A33-6141-20

365A33-6141-21

For blades on which the optional OP61B33 hasbeen embodied, should one or more polyurethaneprotective plates be lost, each flying hourlogged without a protective plate shall becounted double.

AS 365 N3 05-99-002007.12.14 ATA 65-21 Page 3

EASA Approved

00IMPRESDIFF00AS 365 N3 05-99-00---ATA 65-21---2007.12.14---4

als365n3rev011en

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