Airworthiness directives › 2013-08-17
AD 2013-08-17 Airworthiness Directives; Eurocopter France Helicopters
Applicability*9
This AD becomes effective June 5, 2013.
Compliance
(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Gary Roach, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; email gary.b.roach@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC.
Required actions
The subject of this AD is addressed in European Aviation Safety Agency Emergency AD No. 2010-0064-E, dated April 1, 2010.
Unsafe condition
(1) On or before the affected model helicopters reach the hours time-in-service (TIS) listed in Table 1 to Paragraph (e)(1) of this AD or within 10 hours TIS, whichever occurs later, and thereafter at intervals not to exceed 110 hours TIS, using a 10X or higher magnifying glass, inspect the inner angles and flanges of the 9-degree fuselage frame on the right-hand and left-hand sides for a crack in the area depicted in Figure 1 and Figure 2 of Eurocopter Emergency Alert Service Bulletin (EASB) No. 05.00.57, Revision 1, dated March 31, 2010, or Eurocopter EASB No. 05.39, Revision 1, dated March 31, 2010, as applicable to your model helicopter. Table 1 to Paragraph ( e )(1) Helicopter model Hours TIS SA-365N 8,990 SA-365N1 9,990 AS-365N2 3,190 AS 365 N3 2,090 SA-366G1 9,990 (2) If there is a crack, before further flight, repair the frame. Repairing a frame does not constitute terminating action for the repetitive inspection requirements of this AD.
Affected ADs
This AD defines the unsafe condition as a crack in the 9-degree frame, which could result in loss of structural integrity and subsequent loss of control of the helicopter.
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