AD/DAUPHIN/27 Amdt 6 - Tail Rotor Blades

Administered by Department of Infrastructure, Transport, Regional Development, Communications, Sport and the Arts

Legislation au F2006B08738 Not in force Legislative Instrument

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AIRWORTHINESS DIRECTIVE

On the effective date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/DAUPHIN/27 Amdt 5 and issues the following AD under subregulation 39.1 (1) of CASR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.

 

Eurocopter SA 360 and SA 365 (Dauphin) Series Helicopters

 

AD/DAUPHIN/27

Amdt 6


Tail Rotor Blades 10/2004 DM

 

Applicability:  Model SA 365 N1 helicopters, and AS 365 N2, and N3 helicopters, equipped with tail rotor blade part numbers:

 

365A33-2131-all dash numbers, 365A12-0010-all dash numbers, 365A12-0020-all dash numbers.

Requirement:  1. Blades specified in applicability part of this Directive regardless of the climatic operating conditions:

 

  1. Visually check the blade in accordance with paragraph 2.B.1. of Eurocopter Alert Service Bulletin (ASB) AS 365 No. 05.00.17 Edition 1 Revision 1.

 

b.        Check the clearance between the blade tips and the fenestron duct in accordance with paragraph 2.B.4. of ASB No. 05.00.17 Edition 1 Revision 1.

 

2.         Blades specified in applicability part of this Directive, with a serial number below serial number 18912:

 

  1. Blade operated in normal climatic conditions:

 

(i)            Accomplish a tapping-test on the blade in accordance with paragraph

2.B.2.a. of ASB No. 05.00.17 Edition1 Revision.1.

 

(ii)         Accomplish a tapping-test in zone “D” of the blade root suction face in accordance with paragraph 2.B.3. of ASB No. 05.00.17 Edition 1 Revision 1.

 

b.        Blade operated in hot climatic conditions or in tropical and damp atmosphere:

 

(i)            Accomplish a tapping-test:

 

-            In zone “D” of the blade root suction face in accordance with paragraph 2.B.3. of ASB No. 05.00.17 Edition 1 Revision 1.

 

-            In zone “B” and “C” of the blade suction face skin in accordance with paragraph 2.B.2.b. of ASB No. 05.00.17 Edition 1 Revision 1.

 

(ii)         Accomplish a tapping-test in zone “B” and “C” of the blade pressure face skin in accordance with paragraph 2.B.2.c. of ASB No. 05.00.17 Edition 1 Revision 1.

 

3.         Blades part number 365A12-0020-00 with serial number 18912 or subsequent:

 

  1. Blade operated in normal climatic conditions:

 

-            Accomplish a tapping-test on the blade in accordance with paragraph 2.B.3. of ASB No. 05.00.17 Edition 1 Revision 1.

 

-            Accomplish a tapping-test in zone “D” of the blade root suction face in accordance with paragraph 2.b.3. of ASB No. 05.00.17 Edition 1 Revision 1

 

b.        Blade operated in hot climatic conditions or in tropical and damp atmosphere.

 

(i)            Accomplish a tapping-test:

 

-            In zone “D” of the blade root suction face in accordance with paragraph 2.B.3 of ASB No. 05.00.17 Edition 1 Revision 1.

 

-            In zone “B” and “C” of the blade suction face skin in accordance with paragraph 2.B.2.b. of ASB No. 05.00.17 Edition 1 Revision 1.

 

(ii)         Accomplish a tapping-test in zone “B” and “C” of the blade pressure face skin in accordance with paragraph 2.B.2.c. of ASB No. 05.00.17 Edition 1 Revision 1.

 

4.         Blades part number 365A12-0020-02 with serial number 32944 or subsequent, except for serial numbers 32963 through 33091, 33116 through 33187, and 33232 through 33319:

 

  1. For blades with more than 150 total flight hours; remove the blades in accordance with paragraph 2.B.5 of ASB No. 05.00.17 Edition 1 Revision 1.

 

b For blades with less than 150 total flight hours; remove the blades in accordance with paragraph 2.B.5 of ASB No. 05.00.17 Edition 1 Revision 1.

 

Pending removal of the blades, accomplish the measures described in paragraph

1.E.2.a.5. or 1.E.2.A.6 of ASB No. 05.00.17 Edition 1 Revision 1.

 

5.         Blades part number 365A12-0020-02 and –04 that are operated in normal climatic conditions:

 

  1. Blades that not affected by skin bonding in zone ”D” of the blade suction face:

 

(i)            Accomplish a tapping-test:

 

-            In zone “D” of the blade root suction face in accordance with paragraph 2.B.3 of ASB No. 05.00.17 Edition 1 Revision 1.

 

-            n zone “B” and “C” of the blade suction face in accordance with paragraph 2.B.2.b of ASB No. 05.00.17 Edition 1 Revision 1.

 

(ii)         Accomplish a tapping-test in zone “B” and “C” of the blade pressure face skin in accordance with paragraph 2.B.2.c. of ASB No. 05.00.17 Edition 1 Revision 1.

 

b.        Blades that are affected by permissible skin debonding in zone “D” of the blade suction face:

 

(i)            Accomplish a tapping-test in zone “D” of the blade root suction face in accordance with paragraph 2.B.3. of ASB No. 05.00.17 Edition 1 Revision 1.

 

(ii)          Scrap the blade following discovery of skin debonding in zone “D”.

 

6.         Blades part number 365A12-0020-02 and –04 that are operated in hot climatic conditions or in tropical and damp atmosphere:

 

  1. Blades that are not affected by skin debonding in zone “D” of the blade suction face:

 

(i)            Accomplish a tapping-test:

 

-            In zone ”D” of the blade root suction face in accordance with paragraph 2.B.3 of ASB No. 05.00.17 Edition 1 Revision 1.

 

-            In zone “B” and “C” of the blade suction face skin in accordance with paragraph 2.B.2.b. of ASB No. 05.00.17 Edition 1 Revision 1.

 

(ii)         Accomplish a tapping test in zone “B” and “C” of the blade pressure face skin in accordance with paragraph 2.B.2.c. of ASB No. 05.00.17 Edition 1 Revision 1.

 

b.        Blades that are affected by permissible skin debonding in zone “D” of the blade suction face:

 

(i)            Accomplish a tapping-test in zone “D” of the blade root suction face in accordance with paragraph 2.B.3. of ASB No. 05.00.17 Edition 1 Revision 1.

 

(ii)         Scrap the blade following the discovery of skin debonding in zone “D”.

 

7.         Blades held as spares and listed in applicability part of this Directive:

 

On installation of a blade or a tail rotor assembly, accomplish paragraph 1.E.2.a.of ASB No. 05.00.17 Edition 1 Revision 1.

 

Note: DGAC AD F-2004-116 refers.

 

Compliance: 1.a. At each check after the last flight of the day (ALF).

 

1.b. At intervals not to exceed 100 flight hours.

 

2.a.(i) At intervals not to exceed 50 flight cycles or 25 flight hours, whichever occurs first.

 

2.a.(ii) At intervals not to exceed 25 flight hours.

2.b.(i) At each ALF-check, without exceeding 10 flight hours between two checks. 2.b.(ii) At intervals not to exceed 50 flight cycles or 25 flight hours, whichever occurs

first.

 

3.a. At intervals not to exceed 25 flight hours.

 

3.b.(i) At each ALF-check, without exceeding 10 flight hours between two checks. 3.b.(ii) At intervals not to exceed 25 flight hours.

4.a.   Within 10 flight hours after 24 April 2003.

 

4.b.  Upon accumulating 160 flight hours after 24 April 2003. 5.a.(i) At intervals not to exceed 25 flight hours.

5.a.(ii) At intervals not to exceed 100 flight hours.

 

5.b.(i) At each ALF-check, without exceeding 10 flight hours between two checks.

 

5.b.(ii) Within 25 flight hours.

 

6.a.(i) At each ALF-check, without exceeding 10 flight hours between two checks. 6.a.(ii) At intervals not to exceed 100 flight hours.

6.b.(i) At each ALF-check, without exceeding 10 flight hours between two checks. 6.b.(ii) Within 25 flight hours.

The compliance times at requirement 4 are unchanged by this issue. This Amendment becomes effective on 4 August 2004.

Background: This Directive was prompted by an in-flight incident affecting a tail rotor blade on a Model SA 366 G1 helicopter.

 

Amendment 1 expanded affected blade applicability.

 

Amendment 2 further expanded affected blade applicability, amplified initial inspection requirement, and changed the periodicity of the -0010 blades.

 

Amendment 3 reflected revisions of Requirement document and related DGAC AD.

 

Amendment 4 changed the acceptance criteria applicable to skin debonding, and inspection interval for part number 365A12-0020-02 blades.

 

Amendment 5 was prompted by an accident caused by fatigue failure of the Kevlar tie bar of a tail rotor blade.

 

Amendment 6 is issued in response to a new DGAC AD, which was prompted by reports of two further cases of skin debonding on tail rotor blades on helicopters operated in hot climatic conditions or in tropical and damp atmosphere. This Directive reinforces monitoring measures for blades operating in normal climatic conditions and introduces new monitoring measures for blades operated in hot climatic conditions or in tropical and damp atmosphere.

 

Amendment 5 of this Airworthiness Directive became effective on 24 April 2003. Amendment 4 of this Airworthiness Directive became effective on 17 February 1999.

The original issue of this Airworthiness Directive became effective on 21 March 1991.


David Villiers

Delegate of the Civil Aviation Safety Authority 29 July 2004

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 


The above AD is notified in the Commonwealth of Australia Gazette on 4 August 2004.

Overview

The Civil Aviation Safety Authority Act 1998, enacted by the Parliament of Australia, establishes the legal framework for the regulation of civil aviation safety in Australia. This legislation empowers the Civil Aviation Safety Authority (CASA) to ensure the safety of civil aviation through the development and enforcement of safety standards, including the issuance of Airworthiness Directives (ADs). ADs are regulatory measures designed to correct unsafe conditions identified in aircraft or aeronautical products. The Civil Aviation Safety Authority Act 1998 was enacted to address the need for a robust legislative framework to govern the safety oversight of civil aviation activities in Australia, ensuring the protection of the public and promoting efficient and safe aviation operations. The Airworthiness Directive AD/DAUPHIN/27 Amdt 6, issued under the authority of the Civil Aviation Safety Authority Act 1998, addresses the safety concerns related to the tail rotor blades of Eurocopter SA 360 and SA 365 (Dauphin) Series Helicopters. This directive was prompted by reports of skin debonding on tail rotor blades, particularly in helicopters operated in hot climatic conditions or tropical and damp atmospheres, which led to incidents of in-flight failures. The policy objective of this directive is to reinforce the monitoring measures for blades operating under normal conditions and introduce new monitoring measures for blades operated in more challenging environmental conditions, thereby enhancing the overall safety and airworthiness of the affected aircraft.

Scope and Application

This legislative instrument constitutes an Airworthiness Directive (AD) issued under the Civil Aviation Safety Authority (CASA) and pertains to specific Eurocopter SA 360 and SA 365 (Dauphin) Series Helicopters. The AD applies to the model SA 365 N1 helicopters, as well as AS 365 N2 and N3 helicopters, which are equipped with certain tail rotor blade part numbers. The geographic and jurisdictional reach of this AD is within the Commonwealth of Australia, enforcing compliance across the nation as per CASA regulations. The AD mandates specific actions to be taken on the identified aircraft to correct an unsafe condition, detailing requirements such as visual inspections, clearance checks, and tapping-tests on the blades under various climatic conditions and operational circumstances. The compliance intervals and conditions vary based on blade serial numbers and operating environments, with specific timelines for inspections and actions to be carried out. This AD revokes previous amendments and supersedes them with the updated requirements, which were prompted by incidents and reports of blade failures and skin debonding. The directive does not explicitly mention exclusions or exemptions but focuses on stringent monitoring and corrective measures to ensure the airworthiness of the specified helicopters.

Key Provisions

The Airworthiness Directive (AD) issued under the Civil Aviation Act 1988 mandates specific safety measures for certain Eurocopter SA 360 and SA 365 (Dauphin) series helicopters. The AD (AD/DAUPHIN/27 Amdt 6) specifies that the action required by the delegate is necessary to correct an unsafe condition identified in the background section of the legislation. The AD applies to specific models of Dauphin helicopters, namely the SA 365 N1, AS 365 N2, and N3 helicopters equipped with particular tail rotor blades, identified by their part numbers and serial numbers. The directive outlines a series of requirements to ensure the safety and airworthiness of these helicopters, including visual inspections, clearance checks, and tapping tests on the blades, depending on the operating conditions and blade serial numbers. The compliance section details when these checks and tests must be conducted, either after each flight or at specific intervals measured in flight hours or cycles. The AD imposes several obligations on the parties it governs, including helicopter operators and maintenance personnel. Operators must ensure that the specified inspections and tests are conducted in accordance with the detailed instructions provided in the Eurocopter Alert Service Bulletin (ASB) AS 365 No. 05.00.17 Edition 1 Revision 1. Maintenance personnel must perform these checks and tests meticulously, following the procedures outlined in the ASB. The AD also requires that any identified issues, such as skin debonding, are addressed appropriately, which may include scrapping affected blades. Operators must maintain records of all inspections and tests conducted in compliance with the AD, ensuring traceability and accountability for airworthiness. Breach of the requirements set out in this Airworthiness Directive can result in significant legal and safety consequences. Non-compliance with the AD may lead to the grounding of affected helicopters until the required actions are taken, potentially disrupting operations and incurring additional costs. Furthermore, failure to adhere to the AD could compromise the safety of the aircraft, leading to potential accidents and endangering lives. Under the Civil Aviation Act 1988, individuals or entities found in breach of an Airworthiness Directive may face penalties, including fines and potential imprisonment for serious violations. The specific penalties are determined by the severity of the breach and are subject to the regulatory framework governing civil aviation safety in Australia.

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Sourced from the Federal Register of Legislation at 26 August 2026. For the latest information on Australian Government law please go to https://www.legislation.gov.au.