AD 2019-12-14 Airworthiness Directives; Airbus Helicopters Deutschland GmbH Helicopters

This AD becomes effective August 2, 2019.

(1) The Manager, Safety Management Section, Rotorcraft Standards Branch, FAA, may approve AMOCs for this AD. Send your proposal to: Matt Fuller, Senior Aviation Safety Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; email 9-ASW-FTW-AMOC-Requests@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.

(1) Airbus Helicopters Alert Service Bulletin ASB MBB-BK117 C-2-04A-008, Revision 0, dated April 27, 2017, which is not incorporated by reference, contains additional information about the subject of this AD. For service information identified in this AD, contact Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX 75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or at http://www.helicopters.airbus.com/website/en/ref/Technical-Support_73.html. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177. (2) The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2017-0174, dated September 12, 2017. You may view the EASA AD on the internet at http://www.regulations.gov in Docket No. FAA-2018-0980.

Before further flight, remove from service any part that has reached or exceeded its new or reduced life limit as listed in Table 1 to paragraph (e) of this AD. Thereafter, remove from service each part on or before reaching its new or reduced life limit as listed in Table 1 to paragraph (e) of this AD. For purposes of this AD, a “landing” is counted any time the helicopter lifts off into the air and then lands again regardless of the duration of the landing and regardless of whether the engine is shut down. Table 1 to Paragraph ( e ) Part name Part No. (P/N) Life limit Nut B622M1003201 65,800 landings or 10,123 hours time-in-service (TIS) if the number of landings is unknown. Quadruple nut upper Quadruple nut lower B622M1004201 B622M1005201 60,000 landings or 9,230 hours TIS if the number of landings is unknown. Bolt B622M1006201, B622M1007201 31,200 landings or 4,800 hours TIS if the number of landings is unknown. Inner sleeve B622M1009201 13,300 hours TIS. Control ring assembly B623M2001101 27,600 hours TIS. Bellcrank-K (collective) B670M7021201 21,500 hours TIS. Control rod tube B291M1015201 30,000 hours TIS. Forked lever B671M7007201 B671M7007205 22,500 Hours TIS.

This AD defines the unsafe condition as a part remaining in service beyond its fatigue life. This condition could result in failure of a part and loss of control of the helicopter.