Airworthiness Directive · Amendment 39-23213 · Rotorcraft flight control
Airbus Helicopters Deutschland GmbH (AHD) Helicopters
This AD applies to Airbus Helicopters Deutschland GmbH (AHD) Model BO-105A, BO-105C, BO-105S, BO-105LS A-3, MBB-BK 117 A-3, MBB-BK 117 A-4, MBB-BK 117 B-1, MBB-BK 117 B-2, and MBB-BK 117 C-1 helicopters, including those Model BO-105LS A-3 helicopters with FAA Supplemental Type Certificate (STC) SR00043RD installed, certificated in any category.
The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Deutschland GmbH (AHD) Model BO-105A, BO-105C, BO- 105S, BO-105LS A-3, MBB-BK 117 A-3, MBB-BK 117 A-4, MBB-BK 117 B-1, MBB-BK 117 B-2, and MBB-BK 117 C-1 helicopters. This AD was prompted by a report of a crack found on the fork lever of the mixing lever assembly. This AD requires visually inspecting the fork lever for cracks and the mixing lever assembly for missing components, damage, or corrosion. Depending on the results of these inspections, this AD requires taking corrective action and reporting the results of the inspection to the manufacturer. Lastly, this AD prohibits installing affected fork levers unless 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 2025-0217, dated October 1, 2025 (EASA AD 2025-0217).
(1) Where EASA AD 2025-0217 refers to its effective date, this AD requires using the effective date of this AD.
(2) Where EASA AD 2025-0217 specifies compliance in terms of flight hours, this AD requires using hours time-in-service.
(3) Where paragraph (1) of EASA AD 2025-0217 specifies “for condition”, this AD requires replacing that text with “for missing locking devices, deformation, scratches, scrapes, gouges, missing surface finish, bearing play, bearing roughness, or corrosion”.
(4) Where paragraph (3) of EASA AD 2025-0217 specifies any discrepancy, for the purpose of this AD a discrepancy can be defined as any missing components, damage (missing locking devices, deformation, scratches, scrapes, gouges, missing surface finish, bearing play, bearing roughness), or corrosion.
(5) Where the material referenced in EASA AD 2025-0217 specifies “In case of any doubts on the result from the visual inspection, create an Technical Event (TE) on WebTEK for further instructions”, this AD requires replacing that text with “if there is a line having no visible gap or misalignment, before further flight, perform a borescope inspection on the fork lever to determine if the line is a scratch or a crack”.
(6) Where the material referenced in EASA AD 2025-0217 specifies discarding parts, this AD does not require that action.
(7) Where paragraph (4) of EASA AD 2025-0217 specifies to report the inspection results to AHD and that the ASB [Alert Service Bulletin] provides instructions which constitute an acceptable method to comply, for this AD, report results directly to Airbus Helicopters within 10 days after accomplishing the inspection required by this AD.
(8) Where the material referenced in EASA AD 2025-0217 specifies “If the inspection shows no irregular results, proceed with Section 3.B.3”, this AD does not require this action.
(9) This AD does not adopt the “Remarks” section of EASA AD 2025-0217.
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.
