Airworthiness Directive · Amendment 39-21520 · Rotorcraft flight control
Airbus Helicopters Deutschland GmbH Helicopters
This AD applies to Airbus Helicopters Deutschland GmbH Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, and EC135T3 helicopters, certificated in any category, with any of the part numbers specified in paragraphs (c)(1) through (3) of this AD installed.
(1) Longitudinal single-axis actuator part number (P/N) L673M20A1008 or P/N L673M30A2111.
(2) Collective single‐axis actuator P/N L673M20A1012, P/N L673M30A1211, or P/N E673M30A1201.
(3) Lateral single‐axis actuator P/N L673M20A1011 or P/N L673M30A2311.
The FAA is superseding Airworthiness Directive (AD) 2019-17- 02, which applied to certain Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, and EC135T3 helicopters. AD 2019-17-02 required inspecting certain part-numbered actuators for corrosion, removing them as necessary, and reporting certain information. This new AD continues to require inspecting certain part-numbered actuators, removing them as necessary, and reporting; and extends the compliance time for the initial inspection, expands the applicability, and includes new requirements for repetitive replacement of affected actuators; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by a hard landing of a helicopter and the discovery of a ruptured and displaced tie bar inside the piston of the longitudinal single-axis actuator of the main rotor actuator (MRA). The FAA is issuing this AD to address the unsafe condition on these products.
Except as specified in paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, European Union Aviation Safety Agency (EASA) AD 2020-0105, dated May 11, 2020 (EASA AD 2020-0105).
(1) Where EASA AD 2020-0105 refers to its effective date, this AD requires using the effective date of this AD.
(2) Where paragraph (4) of EASA AD 2020-0105 refers to Table 1 of that AD for applicable compliance times, for this AD, use Table 1 to paragraph (h)(2) of this AD.
(3) Where the “part calendar age (A)” and “part calendar age (B)” definitions of EASA AD 2020-0105 refer to March 29, 2019 “(ASB [alert service bulletin] reference date)” and to April 26, 2019 “(the effective date of EASA AD 2019-0087-E, dated April 24, 2019),” this AD requires using April 23, 2019.
(4) The “Remarks” section of EASA AD 2020-0105 does not apply to this AD.
(5) Where the service information referenced in EASA AD 2020-0105 specifies to replace a certain part, this AD requires removing that part from service or repairing using a method approved by the Manager, International Validation Branch, FAA. For a repair method to be approved by the Manager, International Validation Branch, as required by this paragraph, the Manager's approval letter must specifically refer to this AD.
(6) Paragraph (2) of EASA AD 2020-0105 specifies to report inspection results to Airbus Helicopters within a certain compliance time. For this AD, report all inspection results at the applicable time specified in paragraph (6)(i) or (ii) of this AD.
(i) If the inspection was done on or after the effective date of this AD: Submit the report within 7 days after the inspection.
(ii) If the inspection was done before the effective date of this AD: Submit the report within 7 days after the effective date of this AD.
(7) Where paragraph (4) of EASA AD 2020-0105 provides an option to do repetitive replacements or repetitive inspections of an affected part, this AD does not allow the option to do repetitive inspections. However, this AD does allow repetitive repairs as an option to the repetitive replacements specified in paragraph (4) of EASA AD 2020-0105. The repetitive repairs must be done using a method approved by the Manager, International Validation Branch, FAA. For a repair method to be approved by the Manager, International Validation Branch, as required by this paragraph, the Manager's approval letter must specifically refer to this AD.
(8) Where Note 1 of paragraph (4) of EASA AD 2020-0105 permits a non-cumulative tolerance of 6 months to be applied to the interval for the repetitive replacement or inspection of the affected part, this AD requires the repetitive replacement or repair of the affected part at intervals not exceeding 5 years 6 months.
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.
