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:
- 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:
- 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:
- 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:
- 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:
- 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:
- 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.