Airworthiness directives › 2014-07-52
AD 2014-07-52 Airworthiness Directives; Airbus Helicopters (Previously Eurocopter France) Helicopters
Applicability*9
This AD becomes effective June 25, 2014 to all persons except those persons to whom it was made immediately effective by Emergency AD 2014-07-52, issued on March 28, 2014, which contained the requirements of this AD.
Compliance
(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Robert Grant, Aviation Safety Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; email robert.grant@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 (EASA) Emergency AD No. 2014-0076-E, dated March 25, 2014. You may view the EASA Emergency AD on the Internet at http://www.regulations.gov in Docket No. FAA-2014-0334.
Unsafe condition
(1) For helicopters with 640 or more hours time-in-service (TIS) since installation of MOD 07 3215 or since installation of an applicable reinforcement angle, within 10 hours TIS, and thereafter, at intervals not exceeding 10 hours TIS, inspect each reinforcement angle for a crack as depicted in Figure 1 of Airbus Helicopters Emergency Alert Service Bulletin No. 05.00.70 for Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1 helicopters and Airbus Helicopters Emergency Alert Service Bulletin No. 05.00.62 for AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters, both Revision 0 and dated March 24, 2014. (2) If there is a crack, before further flight, repair the reinforcement angle in a manner approved by the manager listed in paragraph (f)(1) of this AD. (3) As an optional terminating action for the repetitive inspections required by paragraph (e)(1) of this AD, at intervals not exceeding 165 hours TIS, remove screw No. 5 from the reinforcement angle, thoroughly clean the area around the hole and inspect the reinforcement angle for a crack. If there is not a crack, reinstall the screw. Sequentially repeat the steps required by this paragraph for screws No. 6 through No. 12. If there is a crack, comply with paragraph (e)(2) of this AD.
Affected ADs
This AD defines the unsafe condition as a crack in a rear structure to tailboom junction frame reinforcement angle (reinforcement angle), which if not detected could result in loss of the tailboom and subsequent loss of control of the helicopter.
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