Airworthiness Directive · Amendment 39-21584 · Tail rotor system
Airbus Helicopters Deutschland GmbH Helicopters
Superseded. A later AD replaced this one: AD 2024-17-01. Comply with the one in force.
This airworthiness directive (AD) applies Airbus Helicopters Deutschland GmbH Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, and EC135T3 helicopters, certificated in any category.
The FAA is superseding Airworthiness Directive (AD) 2016-11-21 for Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model EC135P1, EC135P2, EC135P2+, EC135T1, EC135T2, and EC135T2+ helicopters. AD 2016-11-21 required revising the life limit of certain parts and removing each part that has reached its life limit. This AD continues to require revising the life limits for certain parts and removing each part that has reached or exceeded its life limit and expands the applicability to include Model EC135P3 and EC135T3 helicopters. This AD was prompted by the certification of new helicopter models since AD 2016-11-21 was issued. The FAA is issuing this AD to address the unsafe condition on these products.
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.
(1) Before further flight, establish a life limit for the tail rotor hub body (hub body), part number (P/N) L642A2003102, of 27,400 hours time-in-service (TIS). If you cannot determine the hub body's TIS, follow the instructions in Table 1, Examples and Calculations, Effectivity: The history of the hub body is not known or can't be identified, in Airbus Helicopters Alert Service Bulletin ASB EC135-04A-012, Revision 0, dated September 11, 2017, except where the service information specifies that you contact the manufacturer, you are required to remove the part from service instead.
(2) Before further flight, revise the life limit for each part listed in paragraphs (f)(2)(i) and (ii) of this AD in the Airworthiness Limitations Section (ALS) of the existing maintenance manual for your helicopter and record the revised life limit on the component history card or equivalent record as follows:
(i) For swashplate parts:
(A) The life limit for the ring (control ring), P/N L623M2001213, is 10,700 hours TIS.
(B) The life limit for the cardan ring (two-part), P/N L623M2005205, is 14,300 hours TIS.
(C) The life limit for the bolt (control ring), P/N L671M7001215, is 14,300 hours TIS.
(D) The life limit for the bolt (sliding sleeve), P/N L623M2006206 and P/N L623M2006213, is 14,300 hours TIS.
(ii) For mixing lever gear unit parts:
(A) The life limit for the forked lever assembly, P/N L671M3012102, is 10,400 hours TIS.
(B) The life limit for the hinged support, P/N L671M7003210, is 19,000 hours TIS.
(C) The life limit for the bolt, P/N L671M7001220, is 19,000 hours TIS.
(3) Before further flight, remove from service any part listed in paragraphs (f)(1) and (2) of this AD that has reached or exceeded its revised life limit.
(4) Thereafter, for any part listed in paragraphs (f)(1) and (2) of this AD that has not reached or exceeded its life limit, continue to record the life limit of the part on its component history card or equivalent record and remove any part listed in paragraphs (f)(1) and (2) of this AD from service before the part has reached or exceeded its revised life limit.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
