McDonnell Douglas (Hughes) and Kawasaki
McDonnell Douglas (Hughes) and Kawasaki 369 Series Helicopters
McDonnell Douglas (Hughes) and Kawasaki 369 Series Helicopters
| AD/HU 369/120 | Tail Rotor Blade Abrasion Strip | 10/2008 DM |
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| Applicability: | Model 369A, OH-6A, 369D, 369E, 369F, 369FF, 369H, 369HE, 369HM and 369HS, certificated in any category, with a tail rotor blade installed as follows, including all serial numbers and those T/R blades with an “M” or an “I” painted on the T/R blade root:Helicopter Technology Company, LLC (HTC) part number (P/N) 500P3100-101 and -103, or MDHI P/N 369D21640-501, -503, and -505.HTC P/N 500P3100-301 and -303, or MDHI P/N 369D21641- 501, -503, and -505.HTC P/N 500P3300-501 and -503, or MDHI P/N 369D21643- 501, -503, and -505.HTC P/N 500P3500-701 and -703, or MDHI P/N 369D21642- 501, -503, and -505.Note 1: An "M'' or an "I'' painted on the root of the T/R blade indicates compliance with an Alternate Method of Compliance (AMOC) to Emergency AD 2003-08-51 (AD/HU 369/111), issued by the FAA, Los Angeles Aircraft Certification Office (LAACO) on June 13, 2003 to HTC. The AMOC addressed shot peening of the pitch horn of the T/R assembly. CASA is not able to provide a copy of this AMOC. HTC should be approached for a copy if required. |
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| Requirement: | Accomplish the following actions:1. Inspect the abrasion strip-to-skin bond integrity on each T/R blade using a tap test method in accordance with Part 1- Inspection, in Helicopter Technology Company, LLC (HTC) Mandatory Service Bulletin Notice No. 3100-4R4, dated May 10, 2006 (SB) or later FAA approved revision.Note 2: MD Helicopters Service Bulletins (as applicable to model) SB369D-203R1, SB369E- 097R1, SB369F-082R1, and SB369H-246R1, dated January 23, 2006, refer.2. Modifying each T/R blade in accordance with Mandatory Service Bulletin Notice No. 3100-4R4 by installing a titanium rivet P/N 500P3124-13 at the outboard (tip) end and painting the letter "T'' on the root-end of the T/R blade to indicate the terminating modification has been accomplished is terminating action for the inspection requirements of this AD.Note 3: FAA AD 2008-15-03, effective 3 September 2008 refers. |
| Compliance: | 1. Within 25 hours time-in-service (TIS), unless accomplished previously, and thereafter at intervals not to exceed 25 hours TIS.2. Compliance optional, but completing the terminating modification removes the need for further 25 hourly inspections. |
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| This Airworthiness Directive becomes effective on 3 September 2008. | |
| Background: | This Airworthiness Directive is issued to prevent disbonding and subsequent separation of an abrasion strip from a Tail Rotor blade, which could result in vibration, loss of the Tail Rotor, and subsequent loss of control of the helicopter. |
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David Villiers
Delegate of the Civil Aviation Safety Authority
11 August 2008