Airworthiness Directive · Amendment 39-23072 · Tail rotor control system
Airbus Helicopters Deutschland GmbH Helicopters
This AD applies to Airbus Helicopters Deutschland GmbH Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, EC135T3, and EC635T2+ helicopters, serial numbers 0001 through 1999 inclusive, certificated in any category.
Note 1 to paragraph (c): Helicopters with an EC135P3H designation are Model EC135P3 helicopters, and helicopters with an EC135T3H designation are Model EC135T3 helicopters.
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Deutschland GmbH Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, EC135T3, and EC635T2+ helicopters. This AD was prompted by a report of a loss of the tail rotor controls due to a broken control rod of the yaw actuator. This AD requires visual inspection of the ball pivot, fluorescent penetrant inspection of the control rod, visual inspection and measurement of certain parts of the yaw actuator assembly, and depending on the results of these inspections, corrective actions. This AD also prohibits installing an affected part unless it is a serviceable part and certain requirements are met. 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 AD 2025-0108, dated May 8, 2025 (EASA AD 2025-0108).
(1) Where EASA AD 2025-0108 requires compliance in terms of flight hours, this AD requires using hours time-in-service.
(2) Where EASA AD 2025-0108 refers to its effective date, this AD requires using the effective date of this AD.
(3) Where paragraph (2) of EASA AD 2025-0108 specifies “any discrepancy, as defined in the ASB”, this AD requires replacing that text with “any wear or damage.”
(4) Where the material referenced in EASA AD 2025-0108 specifies to examine the close-tolerance bolt, the input lever, the rod end, the adapter, and the connector cover for wear and damage, for the purposes of this AD damage is defined as specified in paragraphs (h)(4)(i) through (iv) of this AD, as applicable.
(i) Damage for the close-tolerance bolt is defined as deformed or stripped, rounded head; bent, stripped, or missing threads; bent shank; grooves in the shank, corrosion or rust; and gouges.
(ii) Damage for the input lever is defined as deformation or elongated attachment hole; bent flange; gouges; corrosion; and cracks.
(iii) Damage for the rod end is defined as corrosion, gouges, bending, and seizing.
(iv) Damage for the adapter or connector is defined as deformation, elongated attachment holes, gouges, cracks, corrosion, and missing surface coating on the adapter or connector.
(5) Where the material referenced in EASA AD 2025-0108 specifies if the ball pivot shows rough stiffness, hard stops, corrosion, or damage, for the purposes of this AD damage is defined as deformation (bent flanges), gouges, areas of bare metal, or missing finish.
(6) Where paragraph (4) of EASA AD 2025-0108 specifies to report inspection results to Airbus Helicopters Deutschland within certain compliance times, for this AD, report inspection results at the applicable times specified in paragraphs (h)(6)(i) or (ii) of this AD.
(i) For an inspection done on or after the effective date of this AD: Submit the report within 15 days after the inspection.
(ii) For an inspection done before the effective date of this AD: Submit the report within 15 days after the effective date of this AD.
(7) Where the material referenced in EASA AD 2025-0108 specifies actions for non-installed equipment or parts, this AD does not require those actions.
(8) Where the material referenced in EASA AD 2025-0108 specifies to replace an affected part, this AD requires removing an affected part from service and replacing it with a serviceable part.
(9) This AD does not adopt the Remarks section of EASA AD 2025-0108.
Although the material referenced in EASA AD 2025-0108 specifies to return parts to the manufacturer, this AD does not require that action.
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.
