Airworthiness directives › 2014-05-07
AD 2014-05-07 Airworthiness Directives; Airbus Helicopters (Type Certificate Previously Held by Eurocopter France) (Airbus Helicopters)
Applicability*9
This AD supersedes AD 2010-11-51, Amendment 39-16396 (75 FR 50874, August 18, 2010).
Compliance
(1) For helicopters with a lever not marked with an “X” near the P/N, within 10 hours time-in-service (TIS), and thereafter at intervals not to exceed 10 hours TIS, using a mirror and appropriate light source, visually inspect the TGB control lever for a crack as shown in area “A” of Figure 2 of Eurocopter Emergency Alert Service Bulletin No. 05.00.62, Revision 2, dated March 1, 2011 (EASB No. 05.00.62), for Model AS350 helicopters, and Eurocopter Emergency Alert Service Bulletin No. 05.00.57, Revision 2, dated March 1, 2011 (EASB No. 05.00.57), for Model AS355 helicopters. If there is a crack, before further flight, replace each cracked TGB control lever with a TGB control lever with a P/N not listed in paragraph (a) of this AD. (2) For Model AS355N helicopters, within 110 hours TIS, or if the helicopter has reached 100 or more hours TIS, within the next 10 hours TIS, and thereafter at intervals not to exceed 110 hours TIS, using a mirror and appropriate light source, inspect each TGB control lever for a crack as shown in area “C” of Figure 8 of EASB No. 05.00.62 or EASB No. 05.00.57, as applicable to your model helicopter. (3) Within 660 hours TIS, replace each TGB control lever with a reworked TGB control lever marked with an “X” near the P/N or with a TGB control lever with a P/N not listed in paragraph (a) of this AD. (4) For all model helicopters except Model AS355N, within 660 hours TIS, or if the helicopter has reached 605 or more hours TIS within the next 55 hours TIS, and thereafter at intervals not to exceed 660 hours TIS, using a mirror and appropriate light source, inspect each TGB control lever for a crack as shown in area “C” of Figure 8 of EASB No. 05.00.62 or EASB No. 05.00.57, as applicable to your model helicopter. (5) If there is a crack, before further flight, replace each cracked TGB control lever with a TGB control lever with a P/N not listed in paragraph (a) of this AD.
Required actions
(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Robert Grant, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Safety Management Group, 2601 Meacham Blvd., Fort Worth, TX 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.
Unsafe condition
You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time.
Affected ADs
This AD defines the unsafe condition as a crack in the TGB control lever. This condition could result in failure of the TGB control lever, loss of tail rotor control, and subsequent loss of control of the helicopter.
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1