Airworthiness Directive · Amendment 39-22916 · Rotorcraft flight control
Airbus Helicopters Deutschland GmbH Helicopters
This AD applies to Airbus Helicopters Deutschland GmbH Model MBB-BK 117 C-2 helicopters, certificated in any category.
Note 1 to paragraph (c): Helicopters with an MBB-BK 117 C-2e designation are Model MBB-BK 117 C-2 helicopters.
The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Deutschland GmbH Model MBB-BK 117 C-2 helicopters. The FAA previously sent this AD as an emergency AD to all known U.S. owners and operators of these helicopters. This AD was prompted by a report of vibrations of the yaw axis during a hover taxi. This AD requires repetitively inspecting the bolted joint between the cardan- pivot joint assembly and the tail rotor actuator piston rod and, depending on the results, taking corrective action. This AD also prohibits installing certain tail rotor actuators unless its requirements are met. These actions are specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
Except as specified in paragraphs (h) and (i) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, European Union Aviation Safety Agency Emergency AD 2024-0237-E, dated December 9, 2024 (EASA Emergency AD 2024-0237-E).
(1) Where EASA Emergency AD 2024-0237-E requires compliance in terms of flight hours, this AD requires using hours time-in-service.
(2) Where EASA Emergency AD 2024-0237-E refers to its effective date, this AD requires using the effective date of this AD.
(3) Where the material referenced in paragraph (1) of EASA Emergency AD 2024-0237-E states to “use a suitable pen,” this AD requires replacing that text with “use a permanent marker.”
(4) Where paragraph (3) of EASA Emergency AD 2024-0237-E states “discrepancy,” for the purpose of this AD, a “discrepancy” is defined as the lines on the piston rod and the bolt do not stay aligned to each other while rotating the tail rotor actuator, or the line is not aligned on the piston rod, the cardan-pivot joint assembly, the lever assembly, and the bolt after connecting the tail rotor actuator upper control rod and the bellcrank.
(5) Where paragraph (3) of EASA Emergency AD 2024-0237-E states to “contact AH for applicable repair instructions and, within the compliance time specified in those instructions, accomplish those instructions accordingly,” this AD requires replacing that text with “accomplish corrective action in accordance with a method approved by the Manager, International Validation Branch, FAA; or EASA; or Airbus Helicopters Deutschland GmbH's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.”
(6) Where paragraphs (4) and (5) of EASA Emergency AD 2024-0237-E specify accomplishing corrective actions, this AD requires accomplishing corrective actions in accordance with a method approved by the Manager, International Validation Branch, FAA; or EASA; or Airbus Helicopters Deutschland GmbH's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature.
(7) This AD does not adopt the “Remarks” section of EASA Emergency AD 2024-0237-E.
Although the material referenced in EASA Emergency AD 2024-0237-E specifies to submit certain information 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.
