Airworthiness Directive · Amendment 39-21967 · Main rotor system
Airbus Helicopters Deutschland GmbH Helicopters
This AD applies to Airbus Helicopters Deutschland GmbH Model MBB-BK 117D-3 helicopters, certificated in any category.
Note 1 to paragraph (c) of this AD: Model MBB-BK117 D-2 helicopters that have been converted into Model MBB-BK117 D-3 helicopters are Model MBB-BK 117 D-3 helicopters and this AD is also applicable to those helicopters.
The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Deutschland GmbH Model MBB-BK 117 D-3 helicopters. This AD was prompted by reports of a main rotor (M/R) blade lead-lag damper in a tilted position. This AD requires inspecting the Flex Control Unit (FCU), and corrective actions if necessary, as well as rework and re-identification of the bearing pin, as 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 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 2021-0160, dated July 5, 2021 (EASA AD 2021-0160).
(1) Where EASA AD 2021-0160 requires compliance in terms of flight hours, this AD requires using hours time-in-service.
(2) Where EASA AD 2021-0160 refers to its effective date, this AD requires using the effective date of this AD.
(3) Where the service information referenced in EASA AD 2021-0160 specifies to contact Airbus Helicopters or replace the Flex Control Unit (FCU) if you find cracks or damage at the protruding conical end of the integrated bearing sleeve, this AD requires removing the FCU from service and replacing with an airworthy part, or repairing the FCU in accordance with a method approved by the Manager, General Aviation & Rotorcraft Section, International Validation Branch, FAA; or EASA; or Airbus Helicopters' EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.
(4) Where a work card in the service information referenced in EASA AD 2021-0160 specifies performing the corrective action and contacting Airbus Helicopters when discrepancies are found, this AD requires performing the corrective actions as specified in the work card but does not require contacting Airbus Helicopters.
(5) Where a work card in the service information referenced in EASA AD 2021-0160 specifies to do a dye penetrant inspection for the inspection of Zone B of the rotor hub-shaft “if you are not sure there are cracks,” this AD requires performing a dye penetrant inspection.
(6) Where paragraph (5) of EASA AD 2021-0160 specifies “it is allowed to install a hexagonal screw P/N D622M0500207 on any helicopter, provided that installation is accomplished in accordance with the instructions of section 3.D of the ASB, or in accordance with the instructions of an AMM revision which includes the technical content of section 3.D of the ASB,” for this AD replace the text “in accordance with the instructions of section 3.D of the ASB, or in accordance with the instructions of an AMM revision which includes the technical content of section 3.D of the ASB” with “in accordance with the instructions of section 3.D of the ASB, or in accordance with the instructions of an AMM revision which includes the identical content of section 3.D of the ASB.”
(7) This AD does not mandate compliance with the “Remarks” section of EASA AD 2021-0160.
Although the service information referenced in EASA AD 2021-0160 specifies to submit certain information to the manufacturer, this AD does not include that requirement.
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.
