Airworthiness directives › 2021-07-08
AD 2021-07-08 Airworthiness Directives; Airbus Helicopters Deutschland GmbH (Type Certificate Previously Held by Eurocopter Deutschland GmbH and Eurocopter Canada Ltd.) Helicopters
Applicability*9
This AD replaces AD 97-26-02, Amendment 39-10245 (62 FR 65749, December 16, 1997).
Compliance
(1) Before further flight and thereafter at intervals not to exceed 100 hours time-in-service, visually inspect the flange in the ribbed area for cracks using a 5-power or higher magnifying glass in accordance with paragraphs 2.A.1. and 2.A.2. of the Accomplishment Instructions in Eurocopter Deutschland GmbH Alert Service Bulletin No. ASB-BO 105-10-110, dated August 27, 1997. (2) If there is a crack, remove from service the cracked M/R mast and replace it with an airworthy M/R mast.
Required actions
(1) The Manager, International Validation Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the International Validation Branch, send it to the attention of the person identified in paragraph (h)(1) of this AD. Information may be emailed to: 9-AVS-AIR-730-AMOC@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, the FAA suggests 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 cracks in the M/R mast flange (flange). This condition could result in failure of the flange and subsequent loss of control of the helicopter.
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